Lateral Blowing による宇宙往還機基本形状の亜音速領域における空力特性向上の研究

概要

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An experimental study on the improvement of aerodynamic characteristics of basic configuration for winged vehicles with lateral blowing in subsonic flow has been conducted. Wing planform is 75º/45º double delta wing whose cross section is modified NACA0010. Lateral blowing is realized by injecting a pair of sonic jets parallel to the trailing edge of the wing. The experiments have been conducted in the transonic wind tunnel of JAXA (Japan Aerospace Exploration Agency) under the testing condition of free-stream Mach number M∞=0.3, Reynolds number Re=2.14×106, angle of attack α=-15–40º and jet momentum coefficient Cμ=0.0166,0.0295 and 0.0398. The results show that the lift coefficient CL and lift-to-drag ratio L/D are increased by lateral blowing over the wide range of angle of attack. The results suggest that lateral blowing can be useful for the improvement of aerodynamic characteristics of basic configuration for winged vehicles in subsonic flow.
社団法人日本航空宇宙学会の論文
2005-02-05