Numerische Studie zur Reduzierung des Phantom Yaw Effekts an manövrierenden Flugkörpern mittels Aerostrakes

Abstract

This numerical study is about the alleviation of the Phantom Yaw Effect on a pitching missile. A pair of slit shaped side jets, so called aerostrakes is used to force a symmetric separation in the shoulder area of the missile. The unsteady Reynolds averaged Navier-Stokes equation are solved with a two equation turbulence model for a case with and without applied aerostrakes. The missile is pitching sinusoidally with a frequency of 5 Hz between 0° ≤ α ≤ 44 °at Mach 0.8. With the aerostrakes the magnitude of the side force could be reduced. For the side force and the yawing moment a reversal of sign with large amplitudes could be prevented using the aerostrakes. The case with aerostrakes shows also a less pronounced influence of the pitching motion on the relevant aerodynamic coefficients.