Numerical investigation on the Phantom Yaw Effect induced due to small nose deflection

Abstract

The effect of a small nose deformation on the vortex formation on a missile geometry at high angles of attack has been numerically investigated. The closure of the RANS-equation has been done with a two equation turbulence model and solved with the state of the art DLR-TAU-code. For this investigation the boundary layer is considered as fully turbulent. Using radial basis function, the forepart of the missile was deformed in the horizontal plane at different positions along the roll axis. Applying deformations with magnitudes close to measured values on a wind tunnel model, side forces were gained similar to the values of a wind tunnel experiment. Like in the mentioned experiment, the vortex asymmetry could be diminished by a pair of jet-strakes meaning the ejection of narrow side jets at the shoulder area of the body.