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Transonic pressure measurements and comparison of theory to experiment for an arrow-wing configuration. Volume 1: Experimental data report, base configuration and effects of wing twist and leading-edge configurationA wind tunnel test of an arrow-wing-body configuration consisting of flat and twisted wings, as well as a variety of leading- and trailing-edge control surface deflections, was conducted at Mach numbers from 0.4 to 1.1 to provide an experimental pressure data base for comparison with theoretical methods. Theory-to-experiment comparisons of detailed pressure distributions were made using current state-of-the-art attached and separated flow methods. The purpose of these comparisons was to delineate conditions under which these theories are valid for both flat and twisted wings and to explore the use of empirical methods to correct the theoretical methods where theory is deficient.
Document ID
19760003946
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Manro, M. E. (Boeing Commercial Airplane Co. Seattle, WA, United States)
Manning, K. J. R. (Boeing Commercial Airplane Co. Seattle, WA, United States)
Hallstaff, T. H. (Boeing Commercial Airplane Co. Seattle, WA, United States)
Rogers, J. T. (Boeing Commercial Airplane Co. Seattle, WA, United States)
Date Acquired
September 3, 2013
Publication Date
October 1, 1975
Subject Category
Aerodynamics
Report/Patent Number
NASA-CR-132727
D6-42670-2-VOL-1
Accession Number
76N11034
Funding Number(s)
CONTRACT_GRANT: NAS1-12875
PROJECT: RTOP 743-01-12-02
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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