Numerische und experimentelle Untersuchung an einem Überschallflugkörper mit Nasenspike im Hochanstellwinkelbereich

Abstract

A often used method to reduce the wave drag on a blunt body for moderate angle of attack is a spike induced flow separation in front of the nose. Besides this the separation has a positive effect on the heat load of the body. But in general this positive side effect is only valid for laminar separation and reattachment of the shear layer. A deviation from the spike design point can lead to a transitional shear layer accompanied by an increase of the heat flux at the reattachment point This talk deals with numerical simulation of a cylinder with a spiked spherical nose at Mach 2 and 5 and analog short duration wind tunnel experiments. The goal is the comparison of the DLR TAU code and windtunnel experiments at a Reynoldsnumber of 1.500.000. It shows for the numerical simulation that the heat flux is considerable higher compared to a fully laminar shear layer in the experiments.