Japan Aerospace Exploration Agency Supersonic Transport Team, Aviation Program Group
Japan Aerospace Exploration Agency Aerodynamics Research Group, Institute of Aerospace Technology
Japan Aerospace Exploration Agency Supersonic Transport Team, Aviation Program Group
Japan Aerospace Exploration Agency Wind Tunnel Technology Center, Institute of Aerospace Technology
Japan Aerospace Exploration Agency Wind Tunnel Technology Center, Institute of Aerospace Technology
Japan Aerospace Exploration Agency Wind Tunnel Technology Center, Institute of Aerospace Technology
Japan Aerospace Exploration Agency JAXA's Engineering Digital Innovation Center
Mach 5 aerodynamic coefficients for a hypersonic experimental airplane are examined at JAXA 0.5 m hypersonic wind tunnel. Six DOF (Degree Of Freedom) forces for the model are measured and evaluated. CFD (Computational Fluid Dynamics) analyses for the same airframe are performed simulating real flight condition for the experimental airplane. As a result, variations of aerodynamic coefficients on angle of attack for both wind tunnel test and CFD analysis are consistent in general. Large separation region is observed on the upper surface of the body at the wind tunnel test. It is presumed that the difference of aerodynamic coefficients has occurred by the difference in flow separation between the wind tunnel test and CFD. Lateral force coefficient and axial force coefficient are raised with engine installed configuration.
極超音速機のマッハ5空力特性試験
63912000.pdf
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