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A study of wing body blending for an advanced supersonic transportIncreases in supersonic cruise lift drag ratio were sought at Mach numbers 2.2 and 2.7 using wing body planform and thickness blending. Constrained twist and camber optimization was performed in the presence of nacelles. Wing and fuselage thickness distributions were optimized for either minimum volume wave drag or minimum total pressure wave drag. The zero leading edge suction lift drag ratios were determined for three wing planforms. The magnitude of the effect of leading edge suction on attainable lift drag ratio was defined on one planform and estimation of available leading edge suction was made.
Document ID
19810009464
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Goebel, T. P. (Rockwell International Corp. Thousand Oaks, CA, United States)
Bonner, E. (Rockwell International Corp. Thousand Oaks, CA, United States)
Robinson, D. A. (Rockwell International Corp. Thousand Oaks, CA, United States)
Date Acquired
August 11, 2013
Publication Date
March 1, 1980
Publication Information
Publication: NASA. Langley Res. Center Supersonic Cruise Res. 1979, Pt. 1
Subject Category
Aircraft Design, Testing And Performance
Accession Number
81N17987
Funding Number(s)
CONTRACT_GRANT: NAS1-15720
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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IDRelationTitle19810009458Collected WorksSupersonic Cruise Research 1979, part 1
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