摘要
The static rolling aerodynamics of a finned slender body is numerically studied in this paper.Simulation results show a nonlinear uprising of the rolling moment when the angle of attack is greater than 20°in subsonic flows.Asymmetric vortex break down phenomenon on the"horizontal"rudders is found to be responsible for this phenomenon.By introducing the geometric-equivalent angle of attack and geometric-equivalent sweep angle,the cause of the nonlinear rolling moment characteristics can be explained by the delta wing vortex breakdown analysis.
The static rolling aerodynamics of a finned slender body is numerically studied in this paper. Simulation results show a nonlinear uprising of the rolling moment when the angle of attack is greater than 20° in subsonic flows. Asymmetric vortex break down phenomenon on the ＂horizontal＂ rudders is found to be responsible for this phenomenon. By introducing the geometric-equivalent angle of attack and geometric-equivalent sweep angle, the cause of the nonlinear rolling moment characteristics can be explained by the delta wing vortex breakdown analysis.
基金
supported by the National Key Basic Research Program of China(Grant No.2014CB744801)
the National Natural Science Foundation of China(Grant Nos.11102098 and 11372160)
