ACTA AERONAUTICAET ASTRONAUTICA SINICA >
Waverider design for controlled leading and trailing edge
Received date: 2016-02-23
Revised date: 2016-04-05
Online published: 2016-04-06
Supported by
National Natural Science Foundation of China (90916029)
The design method of waverider with controllable leading and trailing edge is proposed in this paper. Based on the external conical basic flowfield with controlled Mach number distribution, the waverider with elliptical leading edge to elliptical trailing edge transition is designed utilizing the streamline tracing technique and blend function. Numerical simulation results at design (Ma=6.0) and relay point (Ma=4.0) indicate that the waverider with controlled leading and trailing edge produces a weaker shock on the acute transition surface. There is a high temperature and pressure section on both sides of the exit plane. The back shock shape near symmetric plane changes from circular arc to straight line and the exit flowfield is essentially uniform, which would be very favorable to match the inlets. Moreover, the waverider is of high volume ratio and precompression efficiency, and the volume ratio after boundary layer correction is 0.24. Also, it has good waverider characteristics on design point, and its forepart rides wave completely on relay point. The lift-drag ratio is high, which is 2.54 and 2.41 for the viscous design and relay point, respectively. In addition, comparison with the waverider with controlled leading edge indicates that the lift force, drag force, pitching moment and exit compression ratio are significantly increased, but the lift-drag ratio and exit total pressure recovery coefficient are decreased. On design point, lift-drag ratio decreases from 3.56 to 3.00 under inviscid condition. In conclusion, this design method is feasible and more flexible, and extends the scope of waverider.
Key words： hypersonic; waverider; curved shock wave; blend function; streamline tracing
LI Yongzhou , SUN Di , ZHANG Kunyuan . Waverider design for controlled leading and trailing edge[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2017 , 38(1) : 120153 -120153 . DOI: 10.7527/S1000-6893.2016.0112
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