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Infinitesimal Conical Supersonic FlowThe calculation of infinitesimal conical supersonic flow has been applied first to the simplest examples that have also been calculated in another way. Except for the discovery of a miscalculation in an older report, there was found the expected conformity. The new method of calculation is limited more definitely to the conical case.
Document ID
20030064044
Acquisition Source
Langley Research Center
Document Type
Other - NACA Technical Memorandum
Authors
Busemann, Adolf (National Advisory Committee for Aeronautics. Langley Aeronautical Lab. Langley Field, VA, United States)
Date Acquired
September 7, 2013
Publication Date
March 1, 1947
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NACA-TM-1100
Report Number: NACA-TM-1100
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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