The scaling relations between the performance parameters of propeller-driven aircraft flying on Mars and Earth are discussed, including the cruising velocity, power required for cruising flight, and propulsive power generated by propellers. The power ratio criterion for feasible cruising flight of propeller-driven aircraft on Mars is proposed, and the relevant design parameters are identified. This criterion is first used to examine the feasibility of typical and nontypical aircraft for cruising flight on Mars, and then applied as a guideline to the preliminary design of the sample Martian aircraft. In addition, the constraints on the rotational speed of a propeller in cruising flight onMars are given, which should be considered in the design of propellers. The methods developed in this paper are also applicable to other space exploration aircraft for Venus and Titan.

[1] Shigeru Obayashi, and Akira Oyama, “Three-dimensional Aerodynamic Optimization with Genetic Algorithm,” Proceedings of the Third ECCOMAS Computational Fluid Dynamics Conference, John Wiley & Sons Ltd, Chichester, the Third ECCOMAS Computational Fluid Dynamics Conference, Paris, France, September 9-13, 1996.
A Genetic Algorithm has been applied to optimize a wing shape for generic subsonic transportation aircraft by using Navier-Stokes computations. To overcome enormous computational time necessary for this optimization, Numerical Wind tunnel at National Aerospace Laboratory, a parallel vector machine with 166 processing elements, was used. Design results indicate feasibility of the present approach for the aerodynamic optimization in advanced computational environments.

[2] Akira Oyama, Shigeru Obayashi, Kazuhiro Nakahashi, and Takashi Nakamura, “Transonic Wing Optimization Using Genetic Algorithm,” AIAA Paper 97-1854, AIAA 13th Computational Fluid Dynamics Conference, Snow mass, Colorado, June 1997.
A Genetic Algorithm (GA) has been applied to optimize a transonic wing shape for generic transport aircraft. A three-dimensional compressible Navier-Stokes (N-S) solver is used to evaluate aerodynamic performance. Designed wings show a tradeoff between an increase of the airfoil thickness driven by a structural constraint and a reduction of the wave drag produced by a shock wave. The present result indicates that GA has found a best feasible solution in the given design constraints.

[3] Akira Oyama, Shigeru Obayashi, Kazuhiro Nakahashi, and Takashi Nakamura, “Euler/Navier-Stokes Optimization of Supersonic Wing Design Based on Evolutionary Algorithm,” Proceedings of the 10th International Conference on Parallel CFD, Hsinchu, Taiwan, May 1998.
This paper presents aerodynamic shape optimization of a supersonic wing for supersonic civil transportation (SST) using an Evolutionary Algorithm (EA) coupled with an Euler/Navier-Stokes code. To overcome enormous computational time necessary for the design, aerodynamic evaluations are parallelized on Numerical Wind Tunnel (NWT) at National Aerospace Laboratory, a parallel vector machine with 166 processing elements. Parallelization of function evaluations in EA is straightforward and its performance is extremely good since most of computational time is used by flow computations. The design result indicates that the present EA successfully minimizes both the induced drag and the volume wave drag in the given design space.

[4] Akira Oyama, Shigeru Obayashi, Kazuhiro Nakahashi, and Naoki Hirose, “Coding by Taguchi Method for Evolutionary Algorithms Applied to Aerodynamic Optimization,” Proceedings of the Fourth ECCOMAS Computational Fluid Dynamics Conference, John Wiley & Sons Ltd, Chichester, the Fourth ECCOMAS Computational Fluid Dynamics Conference, Athens, Greece, September 1998.
A new coding technique using Taguchi method is proposed for Evolutionary Algorithm (EA) applied to an aerodynamic optimization. Taguchi method is used to investigate interactions of design variables and to determine the appropriate coding structure for EA in advance. EA coupled with the new coding technique is then applied to aerodynamic design of a transonic wing. Three-dimensional Navier-Stokes calculation is used for estimation of wing performance.

[5] Shigeru Obayashi, Kazuhiro Nakahashi, Akira Oyama, and Nobuhisa Yoshino, “Design Optimization of Supersonic Wings Using Evolutionary Algorithms,” Proceedings of the Fourth ECCOMAS Computational Fluid Dynamics Conference, John Wiley & Sons Ltd, Chichester, the Fourth ECCOMAS Computational Fluid Dynamics Conference, Athens, Greece, September 1998.
Feasibility of evolutionary computations for supersonic wing design optimization was demonstrated by the single-objective aerodynamic optimization and multiobjective, multidisciplinary optimization. The aerodynamic optimization problem seeks an optimal supersonic wing shape using the Euler equations. The multidisciplinary optimization problem seeks an optimal supersonic wing planform shape using linearized aerodynamics and wing weight algebraic estimation.

[6] Akira Oyama, Shigeru Obayashi, and Kazuhiro Nakahashi, “Encoding Wing Design Parameters for Evolutionary Optimization,” the 36th Aircraft Symposium, International Session, Yokohama, Japan, Proceedings of Aircraft Symposium, pp. 757-760, October 1998.
A new coding technique using factorial design is proposed for Evolutionary Algorithm(EA) applied to an aerodynamic optimization. Coding structure for EA is determined by the epistasis analysis using the factorial design in advance. The present epistasis analysis is applied to aerodynamic design of a transonic wing. The resulting EA succeeded in finding a good compromised design.

[7] Akira Oyama, Shigeru Obayashi, Kazuhiro Nakahashi, and Naoki Hirose “Fractional Factorial Design of Genetic Coding for Aerodynamic Optimization,” AIAA Paper 99-3298, AIAA 14th Computational Fluid Dynamics Conference, Norfolk, Virginia, June 28 - July 1, 1999.
Evolutionary Algorithms (EAs) based on structured coding have been proposed for aerodynamic optimization of wing design. Fractional factorial design is used to investigate interactions of the design variables to determine the appropriate coding structure for EAs in advance. To improve efficiency and accuracy of this approach, parameterization techniques of airfoil shapes are first tested through reproduction of a NASA supercritical airfoil. Their performance is also examined by performing aerodynamic design optimization coupled with a two-dimensional Navier-Stokes code. Finally, three-dimensional wing design is optimized based on a potential flow code and the design result is presented.

[8] Akira Oyama, Shigeru Obayashi, and Kazuhiro Nakahashi, “Wing Design Using Real-Coded Adaptive Range Genetic Algorithm,” Proceedings of 1999 IEEE International Conference on Systems, Man, and Cybernetics, 1999 IEEE International Conference on Systems, Man, and Cybernetics, Tokyo, Japan, October 1999.(2)
Real-coded Adaptive Range Genetic Algorithms (ARGAs) have been developed. The real-coded ARGAs posses both advantages of the binary-coded ARGAs and the use of the floating point representation to overcome the problems of having a large search space that requires continuous sampling. First, the efficiency and the robustness of the proposed approach have been demonstrated by using a typical test function. Then the proposed approach has been applied to an aerodynamic airfoil shape optimization problem. The results confirm that the real-coded ARGAs consistently find better solutions than the conventional real-coded GAs do. The design result is considered to be the global optimal and thus ensures the feasibility of the real-coded ARGAs in aerodynamic designs.

[9] Akira Oyama, Shigeru Obayashi, Kazuhiro Nakahashi, and Takashi Nakamura, "Aerodynamic Optimization of Transonic Wing Design Based on Evolutionary Algorithm," Proceedings of Third International Conference on Nonlinear Problems in Aviation and Aerospace Methods and Software, Third International Conference on Nonlinear Problems in Aviation and Aerospace Methods and Software, DAYTONA BEACH, FLORIDA, May 2000
Evolutionary Algorithm (EA) is applied to a practical three-dimensional shape optimization for aerodynamic design of an aircraft wing. Aerodynamic performances of the design candidates are evaluated by using the three-dimensional compressive Navier-Stokes equations. A structural constraint is introduced to avoid an apparent solution of zero thickness wing for low drag in high speeds. To overcome enormous computational time necessary for the optimization, the computation is parallelized on Numerical Wind Tunnel at National Aerospace Laboratory in Japan, a parallel computer with 166 vector-processing elements. The results ensure the capability of the EA in handling large-scale design optimizations.

[10] Akira Oyama, "Multidisciplinary Optimization of Transonic Wing Design Based on Evolutionary Algorithms Coupled with CFD solver, "CD-Rom Proceedings of ECCOMAS 2000, European Congress on Computational Methods in Applied Sciences and Engineering, Barcelona, Spain, September 2000.
Evolutionary Algorithms (EAs) were applied to multidisciplinary transonic wing design optimizations. Aerodynamic performances of the design candidates were evaluated by using the three-dimensional compressive Navier-Stokes equations to guarantee an accurate model of the flow field. The wing structure is modeled on a box-beam to estimate the wing thickness and wing weight. To overcome enormous computational time necessary for the optimization, the computation was parallelized on Numerical Wind Tunnel at NAL in Japan and NEC SX-4 computers at Computer Center of Tohoku University in Japan. First, a single objective wing design optimization was demonstrated by maximizing L/D with a structural constraint using a real-coded Adaptive Range Genetic Algorithm (ARGA). Because the structural constraint imposed a tradeoff between minimizations of the induced drag and the wave drag, the present ARGA found a compromised but reasonable design. Then, a multiobjective wing design optimization is performed by minimizing both drag and weight with a constraint on CL using a Multiobjective Evolutionary Algorithm (MOEA). Due to the tradeoff between minimization of aerodynamic drag and minimization of weight of wing structure, the solution to this problem is not a single point but a set of compromised designs. The present MOEA successfully captured these solutions that revealed the tradeoff information. These results showed that EAs were promising approach to multidisciplinary optimization problems.

[11] Akira Oyama, Shigeru Obayashi, and Takashi Nakamura, "Real-Coded Adaptive Range Genetic Algorithm Applied to Transonic Wing Optimization," Lecture Notes in Computer Science 1917, Parallel Problem Solving from Nature - PPSN VI, Springer, pp. 712-721, Parallel Problem Solving from Nature VI, PPSN VI, Paris, France, 2000.
Real-coded Adaptive Range Genetic Algorithms (ARGAs) have been applied to a practical three-dimensional shape optimization for aerodynamic design of an aircraft wing. The real-coded ARGAs possess both advantages of the binary-coded ARGAs and the floating-point representation to overcome the problems of having a large search space that requires continuous sampling. The results confirm that the real-coded ARGAs consistently find better solutions than the conventional real-coded Genetic Algorithms do.

[12] Shigeru Obayashi, Akira Oyama, and Takashi Nakamura, "Transonic Wing Design Based on Evolutionary Algorithms Coupled with CFD Solver," Third International Symposium on High Performance Computing, Tokyo, Japan, October 2000.

[13] Akira Oyama, and Meng-Sing Liou, "Multiobjective Optimization of Rocket Engine Pumps Using Evolutionary Algorithm," CD-ROM Proceedings of AIAA CFD Conference, AIAA-2001-2581, 15th AIAA Computational Fluid Dynamics Conference, Anaheim, California, June 11-14, 2001.
Design optimization method for turbopumps of cryogenic rocket engines has been developed. Multiobjective Evolutionary Algorithm is used for multiobjective pump design optimizations. Performances of design candidates are evaluated by using the meanline pump flow modeling method based on the meanline pump flow modeling method based on the Euler turbine equation coupled with empirical correlations for rotor efficiency.
To demonstrate the feasibility of the present approach, single stage centrifugal pump design and multistage pump design optimizations are presented. In both cases, present method obtains very reasonable Pareto-optimal solutions that include some designs outperforming the original design in total head as well as input power by 1%. Detailed observation of the design results also reveals some important design policies in turbopump design of cryogenic rocket engines. These results ensure the feasibility of EA-based design optimization method in this field.

[14] Akira Oyama, and Meng-Sing Liou, "Multiobjective Optimization of a Multi-Stage Compressor Using Evolutionary Algorithm," AIAA-2002-3535, 38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, Indianapolis, Indiana, July 7-10, 2002.
A multiobjective design optimization tool for multistage compressors has been developed. Multiobjective Evolutionary Algorithm is used to handle multiobjective design optimization problems. Performances of compressors are evaluated by using the axisymmetric through-flow code UD0300M that employs the streamline curvature method. To demonstrate feasibility of the present method, a multiobjective optimization of a four-stage compressor design was performed for maximization of the overall isentropic efficiency and the total pressure ratio. Total pressure and solidities at the rotor trailing edges, and flow angles and solidities at the stator trailing edges are considered as design parameters. The present method obtained hundreds of reasonable and uniformly distributed Pareto-optimal solutions that outperformed the baseline design in both objectives. Detailed observation of the Pareto-optimal designs revealed some design criteria for multi-stage compressor designs.

[15]Akira Oyama, Meng-Sing Liou, and Shigeru Obayashi, "Transonic Axial-Flow Blade Shape Optimization Using Evolutionary Algorithm and Three-Dimensional Navier-Stoke Solver," AIAA-2002-5642, 9th AIAA/ISSMO Symposium on Multidisciplinary Analysis and Optimization, Atlanta, Georgia, September 4-6, 2002.
A reliable and efficient aerodynamic design optimization tool using evolutionary algorithm has been developed for transonic compressor blades. A real-coded adaptive-range genetic algorithm is used to improve efficiency and robustness in design optimization. To represent flow fields accurately and produce reliable designs, three-dimensional Navier-Stokes computation is used for aerodynamic analysis.
To ensure feasibility of the present method, aerodynamic redesign of NASA rotor67 is demonstrated. Entropy production is considered as the objective function to be minimized. The computation is parallelized on the SGI ORIGIN2000 cluster at Institute of Fluid Science, Tohoku University, by distributing flow analyses of design candidates to 64 processing elements. The present method successfully obtained a design that reduced entropy production by more than 19% compared with the rotor67 while satisfying constraints on the mass flow rate and the pressure ratio. The use of the present tool for turbomachinery blade design is demonstrated to allow designers to achieve higher aerodynamic efficiency, while shortening design cycle and reducing design costs significantly.

[16] Akira Oyama, Meng-Sing Liou, and Shigeru Obayashi, "High-Fidelity Swept and Leaned Rotor Blade Design Optimization Using Evolutionary Algorithm," AIAA-2003-4091, 16th AIAA Computational Fluid Dynamics Conference, Orlando, Florida, June 23-26, 2003.
In this paper, aerodynamic blade design optimization for a transonic axial compressor has demonstrated by using an evolutionary-algorithm-based high-fidelity design optimization tool. The present method uses a three-dimensional Navier-Stokes solver named TRAF3D for aerodynamic analysis to represent flow fields accurately and the real-coded ARGA for efficient and robust design optimization. The present method successfully obtained a design that reduced entropy production by more than 16% compared with the rotor67 while satisfying constraints on the mass flow rate and the pressure ratio. This study gave some insights into design optimization of a swept and leaned rotor blade for transonic axial compressors.

[17] Akira Oyama, and Meng-Sing Liou, "A Multi-Stage Compressor Design Optimization Using CFD," The 8th Japan-Russia Joint Symposium on Computational Fluid Dynamics, September 25, 2003.
A new constraint-handling method based on Pareto-optimality concept for multiobjective multi-constraint design optimization problems has been proposed. The proposed method does not need any constants to be tuned for constraint handling. In addition, the present method does not use weighted-sum of constraints and thus does not need tuning of weight coefficients and is efficient even when the amount of violation of each constraint is significantly different. The proposed approach is demonstrated to be remarkably robust than the dynamic penalty approach and other dominance-based approaches through the optimal design of a welded beam and conceptual design optimization of a two-stage-to-orbit space plane.

[18] Yong-Sheng Lian, Meng-Sing Liou, and Akira Oyama, "An Enhanced Evolutionary Algorithm with a Surrogate Model," The 2004 Genetic and Evolutionary Computation Conference, Bird-of-a-feather Workshop on Application of Hybrid Evolutionary Algorithms to Complex Optimization Problems, Seattle, Washington, June 26-30, 2004.
In this paper we present an enhanced evolutionary algorithm (EA) to solve computationally expensive design optimization problems. In this algorithm we integrate a genetic algorithm (GA) with a local search method to expedite convergence of the GA. We first use a GA to generate a population of data by evaluating real functions, then we construct computationally cheap surrogate models based on the available data. Thereafter, we perform gradient-based local searches on the surrogate models in lieu of the real functions. We apply the GA and gradient-based method alternatively until an optimum is reached. To guarantee convergence to the original problem, we use a trust region management to handle surrogate models. We investigate the number of points used to construct the surrogate model, number of surrogate model constructed, and number of local search performed. Our numerical results, based on two single-objective problems and one multi-objective optimization problem, demonstrate the advantages of the hybrid GA over pure GAs.

[19] Akira Oyama, and Kozo Fujii, "Airfoil Design Optimization for Airplane for Mars Exploration," J-55, The 3rd China-Japan-Korea Joint Symposium on Optimization of Structural and Mechanical Systems, CJK-OSM3, Kanazawa, Ishikawa, October 30- November 2, 2004.
Aerodynamic design optimization of an airfoil for the Mars exploration airplane has been demonstrated by using an evolutionary algorithm. The adaptive range genetic algorithm is used for efficient and robust design optimization. Two-dimensional Navier-Stokes solver is used for accurate aerodynamic performance evaluation. The present computation is parallelized on the SX-6 vector computers in Institute of Space and Aeronautical Science (ISAS) / Japan Aerospace Exploration Agency (JAXA). The optimized airfoil achieved very high aerodynamic performance. The optimum airfoil for Mars exploration airfoil has extremely thin airfoil thickness and strong camber while an optimum airfoil for typical airplane fly on Earth has substantial airfoil thickness in the front. However, a thin airfoil has disadvantages such as structural weight and fuel tank space (if an engine is used for propulsion). The present optimization indicates necessity of multiobjective design optimization for practical airfoil design for Mars exploration airplane.

[20] Nobuyoshi Fujimatsu, Yoshiaki Tamura, Akira Oyama and Kozo Fujii, "Software for Molecular-sensing Application-oriented Postprocessing," Proceedings of International Workshop on Molecular Imaging for Interdisciplinary Research, Sendai, Japan, November 8-9, 2004, pp.94-95.


[21] Hirofumi Ouchi, Masato Ito, Akira Oyama and Kozo Fujii, Application of Ru(�U)-Complex- Based PSP Measurement To Engineering Problems, Proceedings of International Workshop on Molecular Imaging for Interdisciplinary Research, Sendai, Japan, November 8-9, 2004.


[22] Akira Oyama, Kozo Fujii, Koji Shimoyama, and Meng-Sing Liou, "Pareto-Optimality-Based Constraint-Handling Technique and Its Application to Compressor Design," AIAA2005-4983, the 17th AIAA Computational Fluid Dynamics Conference, Toronto, Ontario, June 6-9, 2005.
A new constraint-handling technique based on Pareto-optimality concept is proposed for evolutionary algorithms to efficiently deal with multiobjective multi-constraint design optimization problems. The essence of the proposed method is to apply non-dominance concept based on constraint function values to infeasible designs and to apply non-dominance concept based on objective function values to feasible designs. The proposed technique does not need any constants to be tuned as the proposed technique does not use weighted-sum of constraints. First, the proposed approach is demonstrated to be remarkably more robust than traditional constraint-handling techniques through the optimal design of a welded beam and conceptual design optimization of a two-stage-to-orbit space plane. Next, high-fidelity aerodynamic design optimization of an axial compressor blade design is demonstrated.

[23] Kozo Fujii, Akira Oyama, Nobuyuki Tsuboi, Motoo, Tsukada, Humihiro Ouchi, Masato Ito, and Koichi Hayashi, "Flow Field Analysis of Under-Expanded Supersonic Jets Impinging on an Inclined Flat Plate - Analysis with PSP/Schlieren Images and CFD Simulations", Proceedings of 2005 ASME Fluids Engineering Division Summer Meeting and Exhibition, pp. 683-691, 2005 ASME Fluids Engineering Division Summer Meeting and Exhibition, FEDSM2005, Houston, Texas, June 19-23, 2005. (3)
Flow fields of Mach number 2.2 jet impinging on an inclined flat plate are experimentally investigated using the Pressure Sensitive Paints (PSP) and Schlieren flow visualization. The flow filed structure is mainly determined by two geometrical parameters (nozzle-plate distance and plate angle against the jet) and one flow parameter (pressure ratio). The results suggest that all the observed flow fields can actually be classified into three types of flow structure based on the three parameters above. As an extension of the authors' earlier work, experiments are carried out for higher plate angles. The new results show the effectiveness and limitation of the classification that we proposed. To find out the flow structure, some of the flow fields are computationally simulated. Good agreement of the pressure distributions with the experiment validates the simulation. Although analysis so far is limited, the result reveals three dimensional complex flow structure that created pressure peaks over the plate surface.

[24] Koji Shimoyama, Akira Oyama, and Kozo Fujii, "A New Efficient and Useful Robust Optimization Approach -Design for Multi-Objective Six Sigma," 2005 IEEE Congress on Evolutionary Computation Proceedings, 1, pp. 950-957, 2005 IEEE Congress on Evolutionary Computation, 2005 IEEE CEC, Edinburgh, United Kingdom, September 2-5, 2005. (5)
An efficient and useful robust optimization approach, design for multi-objective six sigma (DFMOSS), has been developed. The DFMOSS couples the ideas of design for six sigma (DFSS) and multi-objective genetic algorithm (MOGA) to solve drawbacks of DFSS. DFMOSS obtains trade-off solutions between optimality and robustness in one optimization. In addition, it does not need careful parameter tuning. Robust optimizations of a test function and welded beam design problem demonstrated that DFMOSS is more effective and more useful than DFSS.

[25] Akira Oyama, Koji Shimoyama, and Kozo Fujii, "New Constraint-Handling Method for Multi-Objective Multi-Constraint Evolutionary Optimization and Its Application to Space Plane Design," CD-ROM Proceedings of EUROGEN 2005, Evolutionary and Deterministic Methods for Design, Optimization and Control with Applications to Industrial and Societal Problems, EUROGEN 2005, Munich, Germany, 12-14 September 2005.
A new constraint-handling method based on Pareto-optimality concept for multiobjective multi-constraint design optimization problems has been proposed. The proposed method does not need any constants to be tuned for constraint handling. In addition, the present method does not use weighted-sum of constraints and thus does not need tuning of weight coefficients and is efficient even when the amount of violation of each constraint is significantly different. The proposed approach is demonstrated to be remarkably robust than the dynamic penalty approach and other dominance-based approaches through the optimal design of a welded beam and conceptual design optimization of a two-stage-to-orbit space plane.

[26] Akira Oyama, and Kozo Fujii, "A Study on Airfoil Design for Future Mars Airplane," AIAA-2006-1484, 44th AIAA Aerospace Sciences Meeting and Exhibit, Reno, Nevada, January 9-12, 2006.
An optimum airfoil design for future Mars airplane for Mars exploration is obtained by evolutionary computation coupled with a two-dimensional Reynolds-averaged Navier-Stokes solver. The optimized airfoil design is also compared with other airfoil designs optimized at different Reynolds number or at different Mach number to discuss Reynolds number and Mach number effects on airfoil design. These results indicate same important design policies in airfoil design optimization in regard to Reynolds number and Mach number effects.

[27] Masato Ito, Akira Oyama, Kozo Fujii, and Koichi Hayashi, "Flow Field Analysis of Jet Impinging on an Inclined Flat Plate at High Plate Angles", AIAA-2006-1047, 44th AIAA Aerospace Sciences Meeting and Exhibit, Reno, Nevada, January 9-12, 2006.
Flow fields of the supersonic jets impinging on an inclined flat plate at high plate-angles are experimentally investigated using surface pressure measurement with pressure sensitive paint and Schlieren flow visualization. While Type I flow type is dominant at high plate angles, the present research found a new flow type “TYPE I with bubble” at plate angle between 60 and 80 degrees. The flow classification according to L/Ls’ and plate angle indicated that  the constant x/L’s curve doesn’t represent the boundary of Type I and Type II anymore at high plate angles between 60 and 90 probably because Type II flows at low plate angles and high plate angles is different phenomena. This study also indicates that the curve dividing Type I and Type I with bubble regions is same as the curve dividing Type II and Type II with bubble regions.

[28] Genta Imai, Kozo Fujii, and Akira Oyama, "Computational Analyses of Supersonic Flows Over a Delta Wing at High Angles of Attack," 2.5S, the 25th International Congress of the Aeronautical Sciences, ICAS 2006, Hamburg, Germany, September 3-8, 2006.
Supersonic flows over a 65-degrees sweep delta wing with a sharp leading edge at high angles of attack are computationally studied.  Computational simulations with various free-stream Mach numbers show that there is a sudden change in flow fields between the free-stream Mach number of 0.8 and 1.2. Visualized images of the simulation results at different flow conditions show that this nonlinear behavior occurs as expansion waves from the leading edge accelerate the flow and shift the share layer closer to the surface when the Mach number at the leading edge becomes supersonic. The results also show that aerodynamic characteristics have a different trend below and above the free-stream Mach number of 1.0. The sudden change occurs not at the boundary of the classification proposed by the former studies. When the free-stream Mach number becomes supersonic, components of the three-dimensional flow structure such as primary vortex, vortex breakdown and windward flow have different nature, which lead to the nonlinear behavior of aerodynamic characteristics.

[29] Koji Shimoyama, Akira Oyama, and Kozo Fujii, "Robust Aerodynamic Airfoil Design Optimization against Wind Variations for Mars Exploratory Airplane," IAC-06-A3.P.3.07, the 57th International Astronautical Congress, IAC 2006, Valencia, Spain, October 2-6, 2006.
Robust aerodynamic airfoil design optimizations of Mars exploratory airplane against wind variations have been carried out by using DFMOSS coupled with the CFD simulation. The present robust optimization successfully found the airfoil designs with robust aerodynamic performances against wind variations. Obtained airfoil design information about the optimality and the robustness of aerodynamic performances indicated that an airfoil with smaller camber can improve the robustness in lift to drag ratio against the variation of flight Mach number, and an airfoil with larger curvature near the shock wave location can improve the robustness in pitching moment against the variation of flight Mach number.

[30] Koji Shimoyama, Akira Oyama, and Kozo Fujii, "Multi-Objective Optimization for Robust Airfoil Design Considering Design Errors and Uncertainties," Proceedings of the 3rd International Conference on Flow Dynamics, pp. 237-238, The 3rd International Conference on Flow Dynamics, ICFD 2006, Matsushima, Japan, November 7-9, 2006.

[31] Koji Shimoyama, Akira Oyama, and Kozo Fujii, "Multi-Objective Six Sigma Approach Applied to Robust Airfoil Design for Mars Airplane," 9th AIAA Non-Deterministic Approaches Conference, Honolulu, Hawaii, AIAA-2007-1966, 23-26 April, 2007.
A new optimization approach for robust design, design for multi-objective six sigma (DFMOSS) has been developed and applied to robust aerodynamic airfoil design for Mars exploratory airplane. The present robust aerodynamic airfoil design optimization using DFMOSS successfully showed the trade-off information between maximization and robustness improvement in aerodynamic performance by a single optimization run without careful input parameter tuning. The obtained trade-off information indicated that an airfoil with a smaller maximum camber improves robustness of lift to drag ratio, and that with a larger curvature near the shock wave location improves robustness of pitching moment against the variation of flight Mach number.

[32] Akira Oyama, Yoshiyuki Okabe, Kozo Fujii, and Koji Shimoyama, "A Study on Flapping Motion for MAV Design Using Design Exploration," AIAA Infotech@Aerospace 2007 Conference and Exhibit, Rohnert Park, California,  AIAA-2007-2878,  May 7-10, 2007
Aerodynamic knowledge for practical flapping-wing micro air vehicle (MAV) design is obtained by application of the design exploration framework coupled with CFD to a multiobjective aerodynamic design optimization problem of two-dimensional flapping motion of an airfoil. Lift and thrust are maximized while required power is minimized in the design problem.  Pareto-optimal solutions are obtained by a multiobjective evolutionary optimization and analyzed with the self-organizing map.  Aerodynamic performance of each flapping motion is evaluated by a two-dimensional Navier-Stokes solver.  The result reveals tradeoff information between each objective and effect of each design parameters on them.  Analysis of the time histories of lift, thrust, and required power coefficients and corresponding pressure coefficient distribution of the extreme Pareto-optimal solutions leads to useful guidelines for the lift maximization, thrust maximization, and required power minimization.

[33] Akira Oyama, Masato Ito, Genta Imai, Seiji Tsutsumi, Nobuo Amitani, and Kojo Fujii, "Mach Number Effect on Flowfield over a Delta Wing in Supersonic Region," 46th AIAA Aerospace Sciences Meeting and Exhibit, Reno, Nevada, AIAA-2008-0354, January 7-10, 2008.
To understand Mach number effect on flow field over a delta wing with blunt leading edge in supersonic and high angle of attack region, wind tunnel experiments of a 65° delta wing are performed in supersonic and high angle of attack flow conditions at the JAXA’s transonic / supersonic wind tunnel.  Oil flow for surface flow visualization, pressure sensitive paint for surface pressure distribution measurement, and Schlieren images for shock wave visualization are used.  The present results indicate that a delta wing with blunt leading edge can be mixed flow of two different types of flow structure in supersonic and high angle of attack flow region and the location of the boundary of the two types of flow moves toward the apex of the wing as the free-stream Mach number increases.

[34] Akira Oyama, Genta Imai, Akira Ogawa, and Kozo Fujii, "Aerodynamic Characteristics of a Delta Wing at High Angles of Attack," 15th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, Dayton, Ohio, AIAA-2008-2563, April 28 - May 1, 2008.

[35]Naoki Tani, Akira Oyama, and Nobuhiro Yamanishi, "Multi Objective Design Optimization of Rocket Engine Turbopump Turbine," 5th International Spacecraft Propulsion Conference / 2nd International Symposium on Propulsion for Space Transportation, Crete, Greece, May 5-8, 2008.
JAXA is now planning to develop a next generation booster engine named LE-X, which is a successor of LE-7A. From an engine cycle study, the LE-X requires a high efficiency turbine. To achieve this requirement, a feasibility study of multi-objective design optimization with generic algorithm was applied to the turbine blade shape. The optimized results show strong tradeoff between axial-horsepower and entropy-rise within the stage. By use of Self-Organizing MAP (SOM) and correlation function, it is revealed that this tradeoff is primarily derived from outlet blade design, and inlet blade shape also has an influence to axial-horsepower improvement.

[36]Tomoaki Tatsukawa, Akira Oyama, and Kozo Fujii, "Comparative Study of Data Mining Methods for Aerodynamic Multiobjective Optimizations," 8th World Congress on Computational Mechanics (WCCM8) / 5th European Congress on Computational Methods in Applied Sciences and Engineering (ECCOMAS2008), Venice, Italy, June 30 - July 5, 2008.

[37] Roel Muller, Akira Oyama, Kozo Fujii, and Harry Hoeijmakers, "Propulsion by an Oscillating Thin Airfoil at Low Reynolds Number," The Fifth International Conference on Computational Fluid Dynamics, Seoul, Korea, July 7-11, 2008.
This paper describes an investigation of the mechanisms producing thrust for an airfoil performing a pitching or heaving motion in a low Reynolds-number flow (Re=1000, based on chord length) by analysis of numerically obtained flow fields and forces on the airfoil.

[38] Naoki Tani, Akira Oyama, Koichi Okita, and Nobuhiro Yamanishi, "Feasibility Study of Multi Objective Shape Optimization for Rocket Engine Turbopump Blade Design," AIAA-2008-4659, 44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Hartford, CT, July 14-16, 2008.
JAXA is now planning to develop a next generation booster engine named LE-X, which is a successor of LE-7A. From an engine cycle study, the LE-X requires a relatively high efficiency turbopump. To achieve this requirement, a feasibility study of design optimization with generic algorithm was applied to the impeller and turbine blade shape. As the first step, single objective optimization was carried out on the impeller blade design, and the second one was a multi objective optimization on the turbine blade shape. It was concerned that optimization may not be effective in such a highly loaded component, however, each of the optimized result have shown improvement on performance. Especially, multi objective optimization can show tradeoff information for several important parameters, therefore, it can be said that such method is quite useful for the improvement or the developing of high efficiency turbopumps.

[39] Keiichiro Fujimoto, Akira Oyama, Kozo Fujii, Nobuyuki Iizuka, and Koichi Okita, "Visualization and Verification Method for Failure Network Analysis of Space Launch Vehicles," DETC2008-49656, Proceedings of IDETC/CIE 2008, New York, New York, August 3-6, 2008.
Comprehensive failure network analysis method was studied for liquid rocket engine development which includes failure propagation through various types of component interfaces in order to achieve exhaustive enumeration of possible failures and to identify actions to eliminate or reduce the potential failure. New failure network visualization method was developed in order to make it easier to understand complicated failure propagation mechanism among multiple system levels. Verification analysis method is developed in which it is verified all of user-specified component interfaces are contained in the failure network analysis result. The perceived component interface is specified by the analyzer and the failure propagation in the result of failure analysis is summarized in two separate N2 charts. By comparing with these two N2 charts, unperceived component interface and the unconsidered failure propagation can be found. It is found to be promising approach to achieve exhaustive enumeration especially for forgettable component interface.


[40] Kengo Asada, Yoshihiko Ninomiya, Akira Oyama, and Kozo Fujii, "Airfoil Flow Experiment on the Duty Cycle of DBD Plasma Actuator," AIAA-2009-0531, 47th AIAA Aerospace Sciences Meeting, Orlando, Florida, January 5-8, 2009.

[41] Akira Oyama, Taku Nonomura, and Kozo Fujii, "Data Mining of Pareto-Optimal Transonic Airfoil Shapes Using Proper Orthogonal Decomposition," AIAA-2009-4000, 19th AIAA Computational Fluid Dynamics, San Antonio, Texas, June 22-25, 2009.
A new approach to extract useful design information from Pareto-optimal solutions of optimization problems is proposed and applied to an aerodynamic transonic airfoil shape optimization. The proposed approach enables an analysis of line, face, or volume data of all Pareto-optimal solutions such as shape and flow field by decomposing the data into principal modes and corresponding base vectors using proper orthogonal decomposition (POD). Analysis of the shape and surface pressure data of the Pareto-optimal solutions of an aerodynamic transonic airfoil shape optimization problem showed that the optimized airfoils can be categorized into two families (low drag designs and high lift designs), where the lift is increased by changing the camber near the trailing edge among the low drag designs while the lift is increased by moving the lower surface upward among the high lift designs.

[42] Akira Oyama, Taku Nonomura, and Kozo Fujii, "Data Mining of Non-Dominated Solutions Using Proper Orthogonal Decomposition," Proceedings of the 11th Annual Conference on Genetic and Evolutionary Computation, pp. 1935-1936, Association for Computing Machinery, New York, NY, USA, 2009.
A new approach to extract useful design information from non-dominated solutions of real-world multiobjective optimization problems is proposed. The proposed approach enables an analysis of line, face, or volume data that Pareto-optimal solutions have such as flow field and stress distribution by decomposing the data into principal modes using proper orthogonal decomposition. Analysis of the shape and surface pressure data of the non-dominated solutions of an aerodynamic transonic airfoil shape optimization problem shows capability of the proposed approach for design knowledge extraction for real-world design optimization problems.

[43]Takashi Kubota, Naoko Ogawa, Tatsuaki Okada, Hideaki Miyamoto, Mutsuko Yano Morimoto, Kazuhisa Fujita, Tetsuya Yamada, Takahide Mizuno, Yasuhiro Kawakatsu, Akira Oyama, Takehiko Satoh, Jun'ichiro Kawaguchi, "Preliminary Study on Lander System and Scientific Investigation for Next Mars Exploration," ISTS2009-K-21, 27th International Symposium on Space Technology and Science (ISTS 2009), Tsukuba, Japan, July 5-12, 2009.
This paper presents Japanese Mars exploration plan. Firstly the outline of Mars exploration plan, scientific objectives and technological challenges.This paper presents Mars robotics exploration by landers in detail. This paper describes the system design of landers and science investigation. This paper also presents the technical challenges, especially accurate navigation and guidance, reliable landing scheme with obstacle avoidance, surface exploration technology.

[44] Akira Oyama, Paul C. Verburg, Taku Nonomura, Harry W. M. Hoeijmakers, and Kozo Fujii, "Flow Field Data Mining of Pareto-Optimal Airfoils Using Proper Orthogonal Decomposition," AIAA-2010-1140, 48th AIAA Aerospace Sciences Meeting, Orlando, Florida, January 4-7, 2010.
Capability of proper-orthogonal-decomposition-based data mining approach for analysis of flow field data of the Pareto-optimal solutions is demonstrated. This method enables a designer to extract design knowledge by examining baseline data and a limited number of eigenvectors and orthogonal base vectors. The flow data analyzed here are pressure field data of the Pareto-optimal solutions of an aerodynamic transonic airfoil shape optimization problem. The present result shows that the proper-orthogonal-decomposition-based data mining approach is a useful approach for extracting design knowledge from flow field data of the Pareto-optimal solutions.


[45] Weipeng Li, Taku Nonomura, Akira Oyama, and Kozo Fujii, "LES Study of Feedback-loop Mechanism of Supersonic Open Cavity Flows," AIAA-2010-5112, 40th Fluid Dynamics Conference and Exhibit, Chicago, Illinois, June 28-1, 2010.
Supersonic flow over a three-dimensional rectangular cavity with length-to-depth ratio of 2 is numerically studied by implicit large-eddy simulation to clarify the feedback-loop mechanism. A feedback-loop cycle is described and visualized with phase-averaged analysis of simulation results. Causality between the feedback acoustic wave and leading-edge shedding vortex is clearly demonstrated. Mach wave reflection at trailing edge is turned out to be the generation mechanism of feedback acoustic wave. It is convinced by investigating time-series instantaneous flowfields and auto-correlation coefficients of three simulation cases with different convective Mach number. Components of compression waves in supersonic cavity flows are summarized and their features are discussed. Proper orthogonal Decomposition (POD) in frequency domain is firstly employed to analyze wave propagations inside cavity. Results statistically show the propagation traces of notable compression waves inside cavity which are affected by high-speed recirculation flows.

[46] Yoshinori Namera, Ryoji Takaki, Akira Oyama, Kozo Fujii, and Makoto Yamamoto, "Aerodynamic Shape Design of the Vertical Landing Rocket Vehicle," AIAA-2010-4367, 28th AIAA Applied Aerodynamics Conference, Chicago, Illinois, June 28-1, 2010
Aerodynamic characteristics of a vertical landing rocket vehicle are computationally investigated under subsonic and supersonic flight conditions as a preliminary study for the concept design using a light optimization method and a light CFD tool. The results show that the simulations with a coarse grid can accurately estimate the aerodynamic characteristics like axial force coefficient and the lift-to-drag ratio. The results of the light aerodynamic shape optimization indicate tradeoff information among objective functions, and the correlation between design variables and objective functions. The preliminary knowledge for the aerodynamic shape design is obtained.

[47] Yuki Yamazaki, Akira Oyama, Taku Nonomura, Kozo Fujii, and Makoto Yamamoto, "Aerodynamic multiobjective design exploration of flapping wing using a Navier-Stokes solver," International Conference on Computational Fluid Dynamics, St. Petersburg, Russia, July 12-16, 2010.
An aerodynamic design optimization problem of a three-dimensional flapping wing is explored with the multiobjective design exploration framework coupled with a Navier-Stokes solver. The results show that there is a tradeoff among lift maximization, thrust maximization, and required power minimization. The results also show that strong vortex is generated in both down stroke and up stroke motions for thrust maximization while strong vortex is generated only in down stroke motion for lift maximization. This study also reveals effects of the design parameters on the design objectives, for example, pitch offset has positive linear relationship to the lift.

[48] Ryoji Kojima, Taku Nonomura, Akira Oyama, and Kozo Fujii, "Large Eddy Simulation of the Flow over a Thin Airfoil at Low Reynolds Number," International Conference on Computational Fluid Dynamics, St. Petersburg, Russia, July 12-16, 2010.
The performance of airfoil NAXA0002 at Reynolds number of 2.3x10⁴ is investigated with large-eddy simulation. The angle of attack is 3, 6, or 9 degrees. The behavior of a laminar separation bubble which appears over a thin airfoil and its effects on aerodynamic characteristics are mainly discussed.

[49] Koichi Okada, Kozo Fujii, Koji Miyaji, Akira Oyama, Kengo Asada, and Taku Nonomura, "Computational Study of the Synthetic Jet on Separated Flow over a Backward-Facing Step," IMECE2010-38767, ASME International Mechanical Engineering Congress & Exposition, Vancouver, British Columbia, Canada, November 12-18, 2010.

[50] Yukihiro Kosugi, Akira Oyama, Kozo Fujii, Masahiro Kanazaki, "Multidisciplinary and Multi-objective Design Exploration Methodology for Conceptual Design of a Hybrid Rocket", ,Infotech@Aerospace 2011, St. Louis, Missouri, March 2011.

[51] Seiya Ugajin, Akira Oyama, Taku Nonomura, Masaya Suzuki, Makoto Yamamoto, and Kozo Fujii, "Aerodymamic Design Exploration of flapping motion for development of Mars Aircraft," CFD & Optimization, Antalya, Turkey, May 23-25, 2011.

[52] Tomoaki Tatsukawa, Taku Nonomura, Akira Oyama, and Kozo Fujii, "Aerodynamic Design Exploration for Reusable Launch Vehicle Using Genetic Algorithm with Navier-Stokes Solver," The 28th International Symposium on Space Technology and Science, Ginowan, Japan, June 5-12, 2011.

[53] Taro Shimizu, Dan Hori, Keiichi Kitamura, Yu Daimon, and Akira Oyama, "Slit Resonator Design and Damping Estimation in Linear and Non-linear Ranges," AIAA-2001-3261, 41st AIAA Fluid Dynamics Conference and Exhibit, Honolulu, Hawaii, June 27-30, 2011.

[54] Satoshi Sekimoto, Kengo Asada, Tatsuya Usami, Shinichiro Ito, Taku Nonomura, Akira Oyama, and Kozo Fujii, "Experimental Study of Effects of Frequency for Burst Wave on DBD Plasma Actuator for Separation Control," AIAA-2011-3989, 41st AIAA Fluid Dynamics Conference and Exhibit, Honolulu, Hawaii, June 27-30, 2011.

[55] Akira Oyama, "Airplanes for Mars Exploration," 21st Workshop on Astrodynamics and Flight Mechanics, Sagamihara, Kanagawa, July 25-26, 2011.

[56] Akira Oyama, "Multiobjective Design Exploration of Airplane for Mars Exploration," 21st Workshop on Astrodynamics and Flight Mechanics, Sagamihara, Kanagawa, July 25-26, 2011.

[57] Taku Nonomura, Satoshi Sekimoto, Kengo Asada, Akira Oyama, and Kozo Fujii, "Experimental Study of Blowing Direction Effects of DBD Plasma Actuator on Separation Control of Flow Around an Airfoil," ASME-JSME-KSME Joint Fluids Engineering Conference 2011, AJK2011-15010, Hamamatsu, Japan, July 24-29, 2011.

[58] Ryoji Kojima, Donghi Lee, Tomoaki Tatsukawa, Taku Nonomura, Akira Oyama, and Kozo Fujii, "Three-Dimensional Wing Design Towards the Future Mars Airplane," ASME-JSME-KSME Joint Fluids Engineering Conference 2011, AJK2011-15013, Hamamatsu, Japan, July 24-29, 2011.

[59] Ryoji Kojima, Taku Nonomura, Akira Oyama, and Kozo Fujii, "Computational Study of Flow Characteristics of Thick and Thin Airfoil with Implicit Large-eddy Simulation at Low Reynolds Number," ASME-JSME-KSME Joint Fluids Engineering Conference 2011, AJK2011-15026, Hamamatsu, Japan, July 24-29, 2011.

[60] Akira Oyama, Yasuhiro Kawakatsu, and Kazuko Hagiwara, "Application of Multiobjective DEsign Exploration to Solar-C orbit Design," AAS 11-616, the 2011 AAS/AIAA Astrodynamics Specialist Conference, Girdwood, Alaska, July 31- August 4, 2011.

[61] Tomoaki Tatsukawa, Taku Nonomura, Akira Oyama, and Kozo Fujii, "Aerodynamic Design Exploration for Reusable Launch Vehicle Using Multi-Objective Genetic Programming," ASME 2011 International Design Engineering Technical Conferences & Computers and Information in Engineering Conference, Washington, DC, August 28-31, 2011.

[62] Masayuki Anyoji, Taku Nonomura, Akira Oyama, Kozo Fujii, Kei Nose, Daiju Numata, Hiroki Nagai, and Keisuke Asai, "Aerodynamic Characteristics of Ishii Airfoil at Low Reynolds Numbers," Eighth International Conference on Flow Dynamics, Sendai, Japan, November 9-11, 2011.

[63] Naoya Kowatari, Akira Oyama, Hernan Aguirre, and Kiyoshi Tanaka, "A study on Large Population MOEA Using Adaptive Epsilon-Box Dominance and Neighborhood Recombination for Many-Objecitve Optimization, Learning and Intelligent Optimization Conference (LION) 6, Paris France, January 16-20, 2012.

[64] Akira Oyama, "Problem Understanding with Data Mining of Pareto-Optimal Designs in Space Engineering," Dagstuhl Seminar 12041 Learning in Multiobjective Optimization, January 23-27, 2012.

[65] Dan Hori, Taro Shimizu, Keiichi Kitamura, Kazuto Kuzuu, and Akira Oyama, “Slit Resonator Damping Estimation and Proposal of a New Geometry,” 18th AIAA/CEAS Aeroacoustics Conference (33rd AIAA Aeroacoustics Conference), AIAA-2012-2095, 2012.

[66] Tomoaki Tatsukawa, Akira Oyama, and Kozo Fujii, “Extraction of Design Information from Pareto-Optimal Solutions Using Genetic Programming: A First Report,” International Workshop on Future of CFD and Aerospace Sciences, Kobe, Japan, May 23-25, 2012.

[67] Akira Oyama, Yasuhiro Kawakatsu, and Kazuko Hagiwara, “Data Mining of Pareto-Optimal Solutions of a Solar- Observatory Trajectory Design Problem,” Infotech@Aerospace 2012, AIAA-2012-2442 , Orange County, California, June 19-21, 2012.

[68] Naoya Kowatari, Akira Oyama, Hernan Aguirre, and Kiyoshi Tanaka, “Analysis on Population Size and Neighberhood Recombination on Many-Objective Optimization,” 12th International Conference on Parallel Problem Solving from Nature, S7.8, Taormina, Italy, Sep. 1-5, 2012.

[69] Masaki Nakamiya, Satoru Kitani, Akira Oyama, and Yasuhiro Kawakatsu, “Preliminary Study of the Trajectory from the Earth to the Moon with Low Thrust for the Small Scientific Spacecraft, DESTINY,” 63rd International Astronautical Congress, IAC-12.C1.4.4, Naples, Italy, Oct. 1-5, 2012.

[70] Gaku Sasaki, Tomoaki Tatsukawa, Taku Nonomura, Koichi Yonemoto, Akira Oyama, Takaaki Matsumono, and Tomohiro Narumi, “Multi-Objective Numerical Exploration of Airfoil Design for Mars Aircraft,” 5th Symposium on Integrating CFD and Experiments in Aerodynamics, Tokyo, Japan, Oct. 3-5, 2012.

[71] Masaki Nakamiya, Akira Oyama, Mai Bando, Chikako Hirose, Stefano Campangnola, Yasuhiro Kawakatsu, “Trajectory Design from the Earth to the Moon Using the Multi-Objective Optimization for DESTINY Mission,” 23rd International Symposium on Space Flight Dynamics, Pasadena, California, Oct. 29-Nov. 2, 2012.

[72] Gaku Sasaki, Tomoaki Tatsukawa, Taku Nonomura, Koichi Yonemoto, Akira Oyama, and Takaaki Matsumono, “Multi-Objective Optimization of Airfoil in Low Reynolds Number Using Genetic Algorithm,” 2012 Asia-Pacific International Symposium on Aerospace Technology, Jeju, Korea, Nov. 13-15, 2012.

[73] Antonio L ópez, Carlos A. Coello Coello, Akira Oyama, and Kozo Fujii, “An Alternative Preference Relation to Deal with Many-Objective Optimization Problems,” 7th International Conference on Evolutionary Multi-Criterion Optimization, Sheffield, UK, Mar. 19-22, 2013.

[74] Hern án Aguirre, Akira Oyama, and Kiyoshi Tanaka, “Adaptive ε-Sampling and ε-Hood for Evolutionary Many-Objective Optimization,” 7th International Conference on Evolutionary Multi-Criterion Optimization, Sheffield, UK, Mar. 19-22, 2013.

[75] Tomoaki Tatsukawa, Taku Nonomura, Akira Oyama, and Kozo Fujii, “A New Multiobjective Genetic Programming for Extraction of Design Information from Non-Dominated Solutions ,” 7th International Conference on Evolutionary Multi-Criterion Optimization, Sheffield, UK, Mar. 19-22, 2013.

[76] Kazuhisa Fujita, Genya Ishigami, Naoko Ogawa, Akira Oyama, Kazuhiko Yamada, Takashi Kubota, Hirdy Miyamoto, and Takehiko Satoh, "Preliminary Design Study of EDL System for Japan's Mars Rover Mission," 4th INTERNATIONAL ARA DAYS, Arcachon, France, May 27-29, 2013.

[77] Naoya Fujioka, Taku Nonomura, Akira Oyama, Makoto Yamamoto, and Kozo Fujii, "Computational Analysis of Aerodynamic Performance of Mars Airplane," 29th International Symposium on Space Technology and Science, Nagoya, Japan, June 2-9, 2013.

[78] Katsutoshi Kondo, Hikaru Aono, Taku Nonomura, Masayuki Anyoji, Akira Oyama, Tianshu Liu, Kozo Fujii, and Makoto Yamamoto, "Analysis of Owl-like Airfoil Aerodynamics at Low Reynods Number Flow," 29th International Symposium on Space Technology and Science, Nagoya, Japan, June 2-9, 2013.

[79] Gaku Sasaki, Kyoshiro Itakura, Tomoaki Tatsukawa, Taku Nonomura, Koichi Yonemoto, Akira Oyama, and Takaaki Matsumoto, "Multi-Objective Optimization of Airfoil for Mars Exploration Aircraft Using Genetic Algorithm," 29th Innternational Symposium on Space Technology and Science, Nagoya, Japan, June 2-9, 2013.

[80] Bikash Ranjan Das, Junya Aono, Taku Nonomura, Kazuto Kuzuu, Akira Oyama, and Kozo Fujii, "Aerodynamic Effects of Fin Layout on Reusable Vehicle Testing during Gliding Phase," 29th Innternational Symposium on Space Technology and Science, Nagoya, Japan, June 2-9, 2013.

[81] Kazuhisa Fujita, Genya Ishigami, Naoko Ogawa, Akira Oyama, Kazuhiko Yamada, Takashi Kubota, Hirdy Miyamoto, Takehiko Satoh, "Design Study of Mars EDL Demonstrator for MELOS Mission," 29th International Symposium on Space Technology and Science, Nagoya, Japan, June 2-9, 2013.

[82] Naoko Ogawa, Kazunori Ogohara, Kazuhisa Fujita, Takashi Kubota, Genya Ishigami, Akira Oyama, Kazuhiko Yamada, Takehiko Satoh, "Case Study of Trajectory Design for Synergetic Mars Exploration by Orbiter and Lander," 29th International Symposium on Space Technology and Science, Nagoya, Japan, June 2-9, 2013.
[83] Hiroki Nagai, Akira Oyama, and Mars Airplane WG, "Mission Scenario of Mars Exploration by Airplane," The 2013 Adsia-Pacific International Symposium on Aerospace Technology, Nov. 20-22, 2013.
[84] T. Tatsukawa,Y. Nagata, T. Nonomura, A. Oyama, K. Fujii, and M. Yamamoto, "Multiobjective Design Exploration of an Aero-Acoustic Rocket Launch Site Design Problem with Evolutionary Computation and Large Eddy Simulations," SCITECH 2014, National Harbor, Maryland, 13-17 January, 2014.

[85] Yutaka Nishio, Akira Oyama, Youhei Akimoto, Hernan Aguirre and Kiyoshi Tanaka, "Many-objective Optimization of Trajectory Design for DESTINY Mission," Learning and Intelligent Optimization conference, Gainesville, Florida, USA, Feb 16-21, 2014.

[85] Naoko Ogawa, et. al., "Preliminary Trajectory Design of MELOS1 Considering Landing Site Candidates," Astrodynamics Conference, 2013.

[86] Hiroki Nagai, Akira Oyama, and Mars Airplane WG, "Mission Scenario of Mars Exploration by Airplane," The 2013 Adsia-Pacific International Symposium on Aerospace Technology, Nov. 20-22, 2013.
[87] Katsutoshi Kondo, Hikaru. Aono, Taku Nonomura , Akira. Oyama, Kozo. Fujii and Makoto Yamamoto, "Computational Study of Reynolds Number Effect on Owl-like Wing Aerodynamics at Low ," 1502, 5th Asia Pacific Congress on Compuattional Mechanics and 4th International Symposium on Computational Mechanics, Singapole, December, 2013.

[88] T. Tatsukawa,Y. Nagata, T. Nonomura, A. Oyama, K. Fujii, and M. Yamamoto, "Multiobjective Design Exploration of an Aero-Acoustic Rocket Launch Site Design Problem with Evolutionary Computation and Large Eddy Simulations," SCITECH 2014, National Harbor, Maryland, 13-17 January, 2014.

[89] Yutaka Nishio, Akira Oyama, Youhei Akimoto, Hernan Aguirre and Kiyoshi Tanaka, "Many-objective Optimization of Trajectory Design for DESTINY Mission," Learning and Intelligent Optimization conference, Gainesville, Florida, USA, Feb 16-21, 2014.

[90] Takeshi Watanabe, Tomoaki Tatsukawa, Antonio Lopez Jaimes, Hikaru Aono, Taku Nonomura, Akira Oyama, and Kozo Fujii, "Many-Objective Evolutionary Computation for Optimization of Separated-Flow Control Using a DBD Plasma Actuator," 2014 IEEE World Congress on Computational Intelligence, July 6-11, Beijing International Convention Center, Beijing, China.

[91] Hernan Aguirre, Yuki Yazawa, Akira Oyama and Kiyoshi Tanaka, "Extending AeSeH from Many-objective to Multi-objective Optimization," Proceedings of Tenth International Conference on Simulated Evolution and Learning, Dunedin, New Zealand, 15-18 December, 2014.

[92] Tomoaki Tatsukawa, Takeshi Watanabe, Akira Oyama, and Kozo Fujii, "Multiobjective Design Exploration of a Many-objective Space Trajectory Problem for Low-Thrust Spacecraft Using MOEA with Large Populations," AIAA SCITECH 2015, Kissimmee, Florida, Jan 5-9, 2015.

[93] Takeshi Watanabe, Hikaru Aono, Tomoaki Tatsukawa, Taku Nonomura, Akira Oyama, and Kozo Fujii, "Design Exploration of a DBD Plasma Actuator for Massive Separation Control," AIAA SCITECH 2015, Kissimmee, Florida, Jan 5-9, 2015.

[94] Mari Nishiyama,, Hisashi Otake, Takeshi Hoshino, Tatsuaki Hashimoto, Takeshi Watanabe, Tomoaki Tatsukawa, Akira Oyama, "Selection of Landing Sites for Future lunar Missions with Multi-Objective Optimization," 46th Lunar and Planetary Science Conference, The Woodlands, Texas, March 16-20, 2015.