一种空天飞机外形高超声速气动特性实验研究

Experimental Study on Hypersonic Aerodynamic Characteristics of Aerospace Plane Configuration

提供一种空天飞机模型在高超声速风洞中测量的气动力。研究马赫数Ma=4.96,基于模型全长的雷诺数ReL=9×106～15×106;以及Ma=7.96,ReL=5×106来流条件下,攻角α=-5°到α=25°的纵向气动力和横向气动力特性。在Ma=4.96时,着重讨论滚转角和侧滑角变化,以及ReL变化对气动力特性的影响。结果表明,中小攻角下升力和升阻比明显增大,但Ma数增大使升阻比下降。还有,Ma=4.96的数据显示,侧滑角的增大不利于航向稳定。

This paper describes the results of aerodynamic force measurement on the model of an aerospace plane configuration in the hypersonic wind tunnel. The longitudinal and lateral aerodynamic characteristics were obtained for Mach number of 4.96 at Reynolds numbers, based on model length, 9 × 10^6 and 15 × 10^6 , and Mach number of 7.96 at Reynolds number 5 × 10^6 , and angles of attack from - 5°to 25°. At Ma = 4.96 was put emphasis on the effects of rolling angles, yawing angles and Reynolds numbers upon aerodynamics characteristics. The results show that both lift and lift-drag ratio at low-mid values of angle of attack increases rapidly with the increase of angle of attack, but the lift - drag ratio reduces with Maeh number increasing. In addition, the data at Ma = 4.96 exhibits directional unstability as sideslip angles increase.