Experimental and Numerical Studies on the use of Concentrated Energy Deposition for Aerodynamic Drag Reduction Around Re-entry Bodies

Abstract

This paper deals with the effect of electrical energy deposition on the wave drag experienced by a 120° apex angle blunt cone flying at Mach 5.75. The experiments are conducted in the Indian Institute of Science (IISc) hypersonic shock tunnel HST-2. The electrical energy is deposited along the stagnation streamline of the model using a spark discharge system powered by a DC power supply. Drag is measured using a single component accelerometer balance mounted inside the blunt cone model. Illustrative numerical simulations are also carried out by solving the 3-D compressible Navier-Stokes equations, for complimenting the experiments. Results from the parametric numerical studies indicate a substantial reduction in drag (20%~65%) as a result of electrical energy deposition (~ 1 kw; source volume ~ $8e-8m^3)$. Preliminary experimental measurements show ~15% reduction in aerodynamic drag around the reentry body whereas ~45% reduction in drag is predicted by the CFD studies for a similar energy source configuration as used in the experiments.