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Reynolds number effects on the aerodynamic characteristics of irregular planform wings at Mach number 0.3The subsonic aerodynamic characteristics of a series of irregular planform wings were studied in wind tunnel tests conducted at M = 0.3 over a range of Reynolds numbers from 1.6 million to 26 million/m. The five basic wing planforms varied from a trapezoidal to a delta shape. Leading edge extensions, added to the basic shape, varied in approximately 5 deg increments from the wing leading edge sweep-back angle to a maximum 80 deg. Most of the tests were conducted using an NACA 0008 airfoil section with grit boundary layer trips. Tests were also conducted using an NACA 0012 airfoil section and an 8% thick wedge. In addition, the effect of free transition (no grit) was investigated. A body was used on all models.
Document ID
19770021129
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Kruse, R. L. (NASA Ames Research Center Moffett Field, CA, United States)
Lovette, G. H. (NASA Ames Research Center Moffett Field, CA, United States)
Spencer, B., Jr. (NASA Langley Res. Center)
Date Acquired
September 3, 2013
Publication Date
July 1, 1977
Subject Category
Aerodynamics
Report/Patent Number
NASA-TM-X-73132
A-6599
Accession Number
77N28073
Funding Number(s)
PROJECT: RTOP 506-26-31
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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