衝撃波干渉低減を考慮したTSTO型宇宙往還機の母機形状に関する実験的研究

Abstract

This paper presents experimental results of effects of the booster configuration on orbiter aerodynamic characteristics of TSTO type space plane in supersonic region. For booster configurations triangle, square and circle cross sections are selected and blunt and sharp nose shapes are selected. Orbiter is a wing body configuration. Results of optical flow visualizations and orbiter aerodynamic characteristics have been obtained at angle of attack of 0 degree by changing clearance length between the booster and the orbiter. Results of the optical flow visualization show that the strength of shock wave generated by the booster nose depends on the nose configuration and the strength of reflected shock wave by upper surface of the booster depends on the cross section of the booster. And results of 6 components aerodynamic force measurements of orbiter show that significant reduction of variations in lift and pitching moment of the orbiter caused by bow shock wave and reflected shock wave are observed in case of triangle cross section for booster. The orbiter aerodynamic characteristics show that the booster nose shape and fuselage cross-section are significant parameters in TSTO type space plane design for reduction of shock wave interference.