Print Email Facebook Twitter On the determination of optium shapes with finite nose angles Title On the determination of optium shapes with finite nose angles Author Zandbergen, P.J. Institution National Aerospace Laboratory NLR Date 1964-07-01 Abstract This report presents a method for the determination of axially-symmetric shapes with a given base area that are optimum with respect to wave drag in supersonic flow and which have finite nose angles. Use has been made of the exact non-linear differential equations for supersonic flow together with the shock equations. The computed results indicate that the optimum bodies with a finite nose angle have a lower drag than those with cusped noses. This would make their practical application of a certain significance. A number of such shapes have been presented in this report. To reference this document use: http://resolver.tudelft.nl/uuid:3ae68486-3e55-4017-870d-e9ac4f00cc23 Publisher Nationaal Lucht- en Ruimtevaartlaboratorium Access restriction Campus only Source NLR-TR G.30 Part of collection Aerospace Engineering Reports Document type report Rights (c) 1964 National Aerospace Laboratory NLR Files PDF NLR-TR.G.30.pdf 12.51 MB Close viewer /islandora/object/uuid:3ae68486-3e55-4017-870d-e9ac4f00cc23/datastream/OBJ/view