EFFECT OF AERO DISC ON DRAG AND HEAT FLUX ON SUPERSONIC VEHICLE USING COMPUTATIONAL METHOD

Abstract

A forward facing aero-spike attached to a blunt body of a missile and re-entry model changes its flow field and has the potential in drag reduction and wall heat flux. An aero-spike replaces the strong bow shock wave into weaker oblique shock waves and reduces the dynamic pressure in the recirculation region which created upstream of blunt body. In this paper, a blunt body re-entry model represented by hemisphere cylinder placed axis-symmetrically with an aero-disk aero-spike at the stagnation point of blunt body was numerically simulated for different shapes of spikes. The spike consist of 4mm diameter with different aero-disk (hemispherical, flat, flat triangular and inverted flat triangular disk) of varying positions of inner disc(0.2L,0.4L,0.6L and 0.8L) which were numerically simulated. The scaled down geometry has hemisphere cylinder of Diameter (D) 40mm, an overall length 50mm.Numerical simulation has been carried out for single and double aerodisk spike by varying the aero-disk positions.