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An Experimental Study of Hypersonic Wakes Behind Wedges at Angle of Attack


Wu, Jiunn-Jenq (1971) An Experimental Study of Hypersonic Wakes Behind Wedges at Angle of Attack. Engineer's thesis, California Institute of Technology. doi:10.7907/682B-HB46.


Experimental measurements of mean flow properties of hypersonic wakes behind wedges of 20° included angle were conducted for angles of attack up to 25° at Mach number 6, with Reynolds number based on wedge base height ranging from 7000 to 55000. The near and far wake structures were determined, including streamlines and velocity profiles, over a downstream distance of 60 base heights. The base pressure is insensitive to angle of attack within about 17°. At higher incidence, flow separation occurs on the leeward surface. The far viscous wake (x/H Z 4) changes with increasing angle of attack mainly because of the increasing differences of the inviscid flow parameters at the leeward and windward edges of the viscous wake. Transition from laminar to turbulent flow moves upstream as angle of attack increases.

Item Type:Thesis (Engineer's thesis)
Subject Keywords:Aeronautics
Degree Grantor:California Institute of Technology
Division:Engineering and Applied Science
Major Option:Aeronautics
Thesis Availability:Public (worldwide access)
Research Advisor(s):
  • Behrens, Wilhelm
Thesis Committee:
  • Kubota, Toshi (chair)
  • Lees, Lester (chair)
Defense Date:26 March 1971
Funding AgencyGrant Number
U.S. Army Research Office and Advanced Research Projects AgencyDA-31-124-ARO(D)-33
Record Number:CaltechTHESIS:09222010-130843966
Persistent URL:
Default Usage Policy:No commercial reproduction, distribution, display or performance rights in this work are provided.
ID Code:6039
Deposited By: Benjamin Perez
Deposited On:23 Sep 2010 16:48
Last Modified:05 Oct 2021 22:35

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