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Computation of changes in the far flow field due to changes in the nose geometry of a typical fuselage

Authors
  • Srinivas, K
Publication Date
Jun 01, 1980
Source
National Aerospace Laboratories Institutional Repository
Keywords
Language
English
License
Unknown
External links

Abstract

Computations were carried out to determine the effect of changes in nose geometry of a typical fuselage on tho far flow field near the location of external stores where the flow is supersonic. The from stream Mach number was 1.5. r or the particular case considered it was found that the changes in geometry influence the flow field only in the vicinity of the shock and not far downstream where the stores are to be located.

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