Experimental and numerical studies on the use of concentrated energy deposition for aerodynamic drag reduction around re-entry bodies

K. Satheesh, P. S. Kulkami, G. Jagadeesh, Meiu Son, K. Takayama

Research output: Contribution to conferencePaperpeer-review

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-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.

Original languageEnglish
Pages1566-1574
Number of pages9
Publication statusPublished - 2004 Jul 1
Event42nd AIAA Aerospace Sciences Meeting and Exhibit - Reno, NV, United States
Duration: 2004 Jan 52004 Jan 8

Other

Other42nd AIAA Aerospace Sciences Meeting and Exhibit
CountryUnited States
CityReno, NV
Period04/1/504/1/8

ASJC Scopus subject areas

  • Engineering(all)

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