Title: Pressure distributions over a wing-fuselage model at Mach numbers of 0.4 to 0.99 and at 1.2
Abstract: Report presenting pressure distributions over a prolate spheroid of fineness ratio 6 and over a combination of this body with an NACA 65-010 wing section for a range of Mach numbers. Results regarding wall and sting interference, nature of flow over a model in the transonic region, development of supersonic flow from subsonic flow, and a comparison of experimental and theoretical flow at subsonic stream Mach numbers are provided.
Publication Year: 1948
Publication Date: 1948-11-03
Language: en
Type: article
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