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Experiments on Passive Hypervelocity Boundary-Layer Control Using an Ultrasonically Absorptive Surface

Rasheed, A. and Hornung, H. G. and Fedorov, A. V. and Malmuth, N. D. (2002) Experiments on Passive Hypervelocity Boundary-Layer Control Using an Ultrasonically Absorptive Surface. AIAA Journal, 40 (3). pp. 481-489. ISSN 0001-1452. http://resolver.caltech.edu/CaltechAUTHORS:RASaiaaj02

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Abstract

Recently performed linear stability analyses suggested that transition could be delayed in hypersonic boundary layers by using an ultrasonically absorptive surface to damp the second mode (Mack mode). Boundary-layer transition experiments were performed on a sharp 5.06-deg half-angle round cone at zero angle of attack in the T5 Hypervelocity Shock Tunnel to test this concept. The cone was constructed with a smooth surface around half the cone circumference (to serve as a control) and an acoustically absorptive porous surface on the other half. Test gases investigated included nitrogen and carbon dioxide at M∞ ≃ 5 with specific reservoir enthalpy ranging from 1.3 to 13.0 MJ/kg and reservoir pressure ranging from 9.0 to 50.0 MPa. Comparisons were performed to ensure that previous results obtained in similar experiments (on a regular smooth surface) were reproduced, and the results were extended to examine the effects of the porous surface. These experiments indicated that the porous surface was highly effective in delaying transition provided that the pore size was significantly smaller than the viscous length scale.


Item Type:Article
Additional Information:Copyright © 2001 by the authors. Published by the American Institute of Aeronautics and Astronautics, Inc., with permission. Presented as Paper 2001-0274 at the 39th Aerospace Sciences Meeting, Reno, NV, 8–11 January 2001; received 16 February 2001; revision received 4 September 2001; accepted for publication 4 September 2001. This work was sponsored by the Air Force Office of Scientific Research (AFOSR), U.S. Air Force, under AFOSR Grant F49620-98-1-0353 (Steven Walker).
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Air Force Office of Scientific ResearchF49620- 98-1-0353
Record Number:CaltechAUTHORS:RASaiaaj02
Persistent URL:http://resolver.caltech.edu/CaltechAUTHORS:RASaiaaj02
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ID Code:11341
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Deposited On:06 Aug 2008 22:20
Last Modified:19 Sep 2016 17:53

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