Wave drag reduction with a self-aligning aerodisk on a missile configuration

Abstract

In this paper a self-aligning aerodisk to reduce the wave drag on a pitching missile is numerically investigated. The motion and the Mach number were chosen to match a maneuver flight of an actual missile: pitching frequency $f=7.5~Hz$, Mach number $M=2.2$, range of angle of attack $0^\circ<\alpha<21^\circ$. The self-alignment was realized with a coupling of the flow solver with a 6-DOF-tool. In the entire range of angle of attack the drag could be reduced with the self-aligning aerodisk. A comparison with experimental data showed in parts a quite good agreement in the aerodynamic coefficients, in the shock structure and in the alignment of the aerodisk.