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A procedure for the determination of the effect of fuselage nose bluntness on the wave drag of supersonic cruise aircraftThe incremental wave drag penalty due to nose blunting of a fuselage was investigated using a three dimensional finite difference scheme. An aircraft typical of current supersonic cruise concepts was considered. Computational problems with the finite difference scheme as the fuselage afterbody closes were addressed. A linear theory method was employed to compute the afterbody aerodynamics and effectively extends the finite difference scheme to closing afterbodies. Acceptable drag increments for various levels of nose bluntness were demonstrated using this approach.
Document ID
19780010051
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Walkley, K. B. (Vought Corp. Hampton, VA, United States)
Date Acquired
September 3, 2013
Publication Date
January 1, 1978
Subject Category
Aerodynamics
Report/Patent Number
NASA-CR-145306
Report Number: NASA-CR-145306
Accession Number
78N17994
Funding Number(s)
CONTRACT_GRANT: NAS1-13500
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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