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Transonic wall interference effects on bodies of revolution.Efforts to develop a near sonic transport have placed renewed emphasis on obtaining accurate aerodynamic force and pressure data in the near sonic speed range. Comparison of wind-tunnel and flight data obtained for a blunt-nose body of revolution showed significant discrepancies in drag levels near Mach 1 - apparently due to wind-tunnel wall interference. Subsequent tests of geometrically similar bodies of revolution showed that increasing the model-to-test-section blockage ratio from 0.00017 to 0.0043 resulted in altered drag curve shapes, delayed drag divergence, and 'transonic creep' from subsonic drag levels due to increased wall interference.
Document ID
19720061738
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Couch, L. M.
(NASA Langley Research Center Hampton, Va., United States)
Date Acquired
August 6, 2013
Publication Date
September 1, 1972
Subject Category
Facilities, Research, And Support
Report/Patent Number
AIAA PAPER 72-1008
Accession Number
72A45404
Distribution Limits
Public
Copyright
Other

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