NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Collections About News Help Login
Back to Results
An Investigation of the Maximum Lift of Wings at Supersonic SpeedsThis report presents the results of an exploratory investigation carried out in the Langley 9-inch supersonic tunnel to determine the maximum lift of wings operating at supersonic speeds. A variety of wing plan forms of random thickness distributions were tested at Mach numbers of 1.55, 1.90, and 2.32 and at Reynolds numbers varying between 0.74 x 10(6) and 0.27 x 10(6) at angles of attack ranging from zero up through the angle at which maximum lift occurred. Subsequent pressure-distribution tests on wings of triangular and rectangular plan forms were made at a Mach number of 2.40. The results of these tests substantiated the values of maximum lift obtained during the force tests and further showed no appreciable center-of-pressure shift over the entire angle-of-attack range.
Document ID
19930092236
Acquisition Source
Legacy CDMS
Document Type
Other
Authors
Gallagher, James J
Mueller, James N
Date Acquired
September 6, 2013
Publication Date
January 1, 1955
Report/Patent Number
NACA-TR-1227
Accession Number
93R21526
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

Related Records

IDRelationTitleNACA-RM-L7J10Superseded By
No Preview Available