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Computer application of a linearised supersonic lifting surface theory on a certain class of wings

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Author: Labrujere, Th.E.
Publisher: Nationaal Lucht- en Ruimtevaartlaboratorium
Institution: National Aerospace Laboratory NLR
Source:NLR-TR G 50
Rights: (c) 1969 National Aerospace Laboratory NLR


A computer program has been prepared for the determination of the pressure distribution on a thin wing in supersonic flow. The applicability of the program is restricted to cases with completely supersonic trailing edges in the absence of interacting subsonic regions. The present report describes the theory, the numerical evaluation and the computer program and gives some numerical results.