Published in

46th AIAA Aerospace Sciences Meeting and Exhibit

DOI: 10.2514/6.2008-592

American Institute of Aeronautics and Astronautics, Journal of Spacecraft and Rockets, 6(45), p. 1106-1116, 2008

DOI: 10.2514/1.38005

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Effect of Freestream Noise on Roughness-Induced Transition for the X-51A Forebody

Journal article published in 2008 by Matthew P. Borg, Steven P. Schneider, Thomas Juliano
This paper was not found in any repository, but could be made available legally by the author.
This paper was not found in any repository, but could be made available legally by the author.

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Abstract

A 20%-scale X-51A forebody model was tested in the Boeing and U.S. Air Force Office of Scientific Research Mach-6 Quiet Tunnel. The effect of a smooth blank and two different trip strips on windward-forebody transition was measured using temperature-sensitive paint and hot-wire anemometry. Reducing freestream noise from conventional to quiet levels increased the smooth-wall transition Reynolds number by a factor of at least 2.2. In addition, the transition Reynolds number based on the distance from the trips increased by a factor of 2.4 for the smaller trips and by a factor of 1.7 for the larger trips. Thus, tunnel noise had a substantial effect on roughness-induced transition.