Numerical study on the Impact of a maneuver in the Phantom-Yaw-Effect in transonic flow

Abstract

The impact of a dynamic maneuver on the Phantom-Yaw-Effect has been investigated numerically using the finite volume flow solver DLR-TAU-Code. URANS-simulations have been carried out for a generic missile configuration undergoing a sinusoidal pitching motion between an angle of attack of 0° and 44° with a reduced frequency of k=0.0042 at a Mach number of M=0.8. In addition, simulations at fixed angle of attack were performed. The Phantom Yaw Effect itself was triggered due to a slight deformation of the missile. It was found that the magnitude and the angular position of the peak values of the arising side forces are significantly influenced by the maneuver. On the other hand the general development of the Phantom-Yaw-Effect as a function of angle of attack does not change fundamentally with the pitching motion, except near the upper inflection point of the sine movement. An investigation using a locally forced symmetric boundary layer separation close to the nose changed the Phantom-Yaw-Effect in a positive manner and reduced the arising side force.