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Experimental Pressure Distributions on Axisymmetric Cowls at Mach Numbers From 0.60 to 0.92Pressure distributions on four nacelle cowl models of the same length and highlight area but different geometries external to the highlight are compared. The diameter ratio (ratio of highlight diameter to maximum diameter) of the four cowls was 0.854 and the length ratio (ratio of cowl length to maximum diameter) was 0.439. The cowls had the same internal geometry from the highlight to the throat with a contraction ratio (ratio of highlight area to throat area) of 1.250. Data for two other cowls which had a diameter ratio of 0.880, a length ratio of 0.400 and a contraction ratio 1.250 are also included. All the cowls had rows of static pressure orifices on the top and bottom surfaces. Mass-flow ratio was varied between 0.27 and 0.93. Some data were obtained between angles of attack from -2.1deg and 4.1deg. The test was conducted in the Langley 16-Foot Transonic Tunnel.
Document ID
20060026535
Acquisition Source
Langley Research Center
Document Type
Technical Memorandum (TM)
Authors
Re, Richard J. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 7, 2013
Publication Date
August 1, 2006
Subject Category
Aerodynamics
Report/Patent Number
NASA/TM-2006-214313
L-19261
Funding Number(s)
WBS: WBS 581-02-08-07
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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