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An experimental study of the hypersonic aerodynamics of delta wings. (1971)

Rao, D. M.

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Publication Date: 2011-08-16

Description: Results of aerodynamic balance and pressure measurements carried out in a hypersonic gun tunnel (at a free-stream Mach number of 8.2 and a Reynolds number of 800,000) on delta wings having sharp leading edges swept at 70 and 76 deg. The experimental force and pressure coefficients and shock angles are discussed in relation to simple prediction methods. Some transition data are also included.

Keywords: AERODYNAMICS

Type: Aeronautical Society of India; vol. 23

Format: text

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