噴射を用いた宇宙往還機基本形状の空力性能向上の研究
研究申込者
麻生 茂 ( 九州大学 )
Abstract
An experimental study on the improvement of aerodynamic characteristics of wing-body configuration RLVs (Reusable Launch Vehicles) due to lateral blowing has been conducted. Two fuselage-cross sections have been considered: a square and a triangular cross sections with rounded corners. The models have single-delta wings of modified NACA0010 with 45° sweepback angle. Lateral blowing is realized by injecting a pair of sonic jets parallel to the trailing edge of the wing. Experiments have been conducted in the wind tunnel of ISAS (Institute of Space and Astronautical Science), JAXA (Japan Aerospace Exploration Agency) under a test condition of free-stream Mach number M∞=0.3, Reynolds number Re=3.1×10６, angle of attack α= 0°～40° and jet momentum coefficient Cμ=0.02. Results show that lateral blowing increases lift of the models over a wide range of angle of attack. Especially a significant increase in lift is achieved in the case of a "square" model at high angle of attack, as compared to a "triangular" model. Using the experimental results, we evaluate the effects of the fuselage-cross section for RLVs on aerodynamic characteristics from lateral blowing. And we confirmed that lateral blowing is useful for lift augmentation of RLVs in subsonic flow.
Key words
Lateral blowing, Reusable launch vehicles, Aerodynamic characteristics, Fuselage-cross sections
2005年度の研究成果
Kenji Tadakuma, Takuro Ishida, Shigeru Aso and Yasuhiro Tani：Lift Augmentation by Lateral Blowing for RLVs with Various Fuselage-Cross Sections, 3rd AIAA Flow Control Conference, AIAA 2006-3015, Hyatt Regency San Francisco at Embarcadero Center, San Francisco, California, 5 - 8 Jun 2006.
利用期間
平成17年10月3日～10月7日