The waverider with high lift-drag ratio was designed by the inverse-design method based on inviscid conical shock wave. When the basic conical shock wave is 12°, an effective improvement of the lift-drag ratio was obtained for the effect of the decrease of the pressure on the upper surface of the waverider. As the result of the figuration optimization, the value of lift-drag ratio increased to 4.598?1 from 3.356?3 taking account of the viscous effect at Mach 6. An hypersonic configuration of the single-stage-to-orbit(SSTO) adopting the waverider with high lift and low drag as the body was designed. Through the way of numerical simulation, the primary result shows that this configuration with static stability has a satisfying value of L-D ratio.
Blankson M. Air-breathing hypersonic cruise prospects for mach 4-7 waverider[J].Journal of Engineering for Gas Turbines and Power.1994,116(1):104-115
Rasmussen M L. Waverider configurations derived from inclined circular and elliptic cones[J].Spacecrift.1980,17(6):537-545
�� ,Ǯ���. �˲����������[J]. �������պ����ѧѧ��, 1999,25(2):180~183 Wang Zhuo, Qian Yiji. Waverider configuration design[J]. Journal of Beijing University of Aeronautics and Astronautics,1999,25(2):180~183(in Chinese)
��˹W D,���岼˹̹R F. �߳�����������(��һ�� ��ճ��) [M]. ������,���ķ���. ����:��ѧ������,1979 Hayes W D, Probstein R F. Hypersonic flow theory (Vol.1 inviscid flows)[M]. Translated by Yan Zongyi,Sun Shufen. Beijing:Science Press, 1979(in Chinese)
���з�,��˼��.�ɻ��������[M].����:�������պ����ѧ������,2001.27~62 Gu Songfen, Xie Sikuo. The aircraft design[M].Beijing:Beijing University of Aeronautics and Astronautics Press,2001. 27~62(in Chinese)