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-8m3). 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.
|Number of pages||9|
|Publication status||Published - 2004 Jul 1|
|Event||42nd AIAA Aerospace Sciences Meeting and Exhibit - Reno, NV, United States|
Duration: 2004 Jan 5 → 2004 Jan 8
|Other||42nd AIAA Aerospace Sciences Meeting and Exhibit|
|Period||04/1/5 → 04/1/8|
ASJC Scopus subject areas