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Results of Tests to Determine the Effect of a Conical Windshield on the Drag of a Bluff Body at Supersonic SpeedsTests to evaluate the effect of a conical windshield on the drag of a bluff body at supersonic speeds were performed for the following configurations: a sharp nose fuselage with stabilizing fins,a blunt nose fuselage with a hemispherical shape, and a blunt nose fuselage with a conical point. Results of the drag coeeficient are described at Mach 1.0 and the greatest Mach number of 1.37.
Document ID
20030063943
Acquisition Source
Langley Research Center
Document Type
Other - NACA Research Memorandum
Authors
Alexander, Sidney R. (National Advisory Committee for Aeronautics. Langley Aeronautical Lab. Langley Field, VA, United States)
Date Acquired
September 7, 2013
Publication Date
January 14, 1947
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
NACA-RM-L6K08a
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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