Print Email Facebook Twitter Computer application of a linearised supersonic lifting surface theory on a certain class of wings Title Computer application of a linearised supersonic lifting surface theory on a certain class of wings Author Labrujere, Th.E. Institution National Aerospace Laboratory NLR Date 1960-07-30 Abstract 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. To reference this document use: http://resolver.tudelft.nl/uuid:49bdc76c-0ef9-433b-a3b1-17d190596e6b Publisher Nationaal Lucht- en Ruimtevaartlaboratorium Access restriction Campus only Source NLR-TR G 50 Part of collection Aerospace Engineering Reports Document type report Rights (c) 1969 National Aerospace Laboratory NLR Files PDF NLR-TR.G.50.pdf 22.13 MB Close viewer /islandora/object/uuid:49bdc76c-0ef9-433b-a3b1-17d190596e6b/datastream/OBJ/view