Aerodynamic Analysis of a Spinning Missile Using a High-Order Unstructured-Grid Scheme

作者：Sheng Chunhua^*; Wang Xiao; Zhao Qiuying

来源：Journal of Spacecraft and Rockets, 2010, 47(1): 81-89.

DOI：10.2514/1.42988

Time-accurate viscous flow simulations are carried out for a canard-controlled missile in which the missile body spins at a constant roll rate while the canards are dithering. Unsteady Reynolds-averaged Navier-Stokes equations are solved using an arbitrary Mach number algorithm based on unstructured-grid topology and embedded dynamic moving-grid technique for complex missile configuration with movable control surfaces. A new higher-order flux reconstruction scheme is investigated and compared with the original second-order scheme for resolving the complicated flowfield associated with the missile control surfaces (canards). The numerical simulations revealed the formation of a pair of counter-rotating vortices induced by each canard, which interact with the tail fin shocks and boundary layers on the body. A grid refinement study is carried out to assess the efficacy of the high-order spatial discretization in resolving vortex-dominant flows. The computational results show that the higher-order flux reconstruction method introduced in the present study noticeably reduces the numerical dissipation of vortical flows encountered by the conventional second-order schemes and thus significantly reduces the computational costs for the aerodynamic simulation of the spinning missile.

• 出版日期2010-2