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Note on the Wave Drags of Untapered Wings with Streamwise Tips at Zero Lift
Published online by Cambridge University Press: 07 June 2016
Extract
Detailed calculations based on linearised supersonic flow theory have demonstrated in a number of cases the equivalence between the wave drags of yawed or swept wings of constant section and zero lift and the corresponding values in two-dimensional flow. These results and others are shown to follow readily from a general theorem for which a simple proof is given. Some interesting deductions are illustrated in Fig. 3.
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- Research Article
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- Copyright © Royal Aeronautical Society. 1956
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