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Measured Pressure Distributions and Shock Shapes on a Simple Delta Wing
Published online by Cambridge University Press: 07 June 2016
Summary
This note presents the results of an experimental investigation of the flow over a simple delta wing designed for a Mach number of 3.5. Complete pressure distributions were measured for incidences of 0°, 10° and 20° at Mach numbers of 2.5 and 3.5. A number of schlieren photographs of the shock system around the wing were obtained at the same conditions and surface streamline patterns were studied at M = 3.5. The measurements were made to support numerical calculations which use this wing as a test case.
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- Research Article
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- Copyright © Royal Aeronautical Society. 1981
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