Numerical investigation on the development of the Phantom Yaw Effect on a maneuvering missile

Abstract

The aerodynamics of a pitching slender body at $M=0.8$ with two different pivot locations have been numerically investigated using URANS with a two equation turbulence model. Identical to an experiment a sinusoidal motion between $\alpha=0^\circ$ and $44^\circ$ was defined. Due to a deflection of the symmetric numerical grid a vortex asymmetry the so called Phantom Yaw Effect was triggered. While the lift and drag are highly dependent on the pivot the side force and the yawing moment are less sensitive to the pivot. With the help of a forced symmetric separation at the nose the Phantom Yaw Effect could be reduced and the load change at higher angles of attack could be eliminated. A comparison with experimental shows a less good agreement.