Satheesh, K and Kulkami, P and Jagadeesh, G and Sun, M and Takayama, K (2004) Experimental and Numerical Studies on the use of Concentrated Energy Deposition for Aerodynamic Drag Reduction Around Re-entry Bodies. In: 42nd AIAA Aerospace Sciences Meeting and Exhibit, 5-8 January, Reno, Nevada, pp. 1566-1574.
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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.
|Item Type:||Conference Paper|
|Additional Information:||Copyright of this article belongs to American Institute of Aeronautics and Astronautics.|
|Department/Centre:||Division of Mechanical Sciences > Aerospace Engineering (Formerly, Aeronautical Engineering)|
|Date Deposited:||25 Aug 2008|
|Last Modified:||19 Sep 2010 04:32|
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