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Tabulated Pressure Data for a Series of Controls on a 40 Deg Sweptback Wing at Mach Numbers of 1.61 and 2.01An investigation has been made at Mach numbers of 1.61 and 2.01 and Reynolds numbers of 1.7 x l0(exp 6) and 3.6 x l0(exp 6) to determine the pressure distributions over a swept wing with a series of 14 control configurations. The wing had 40 deg of sweep of the quarter-chord line, an aspect ratio of 3.1, and a taper ratio of 0.4. Measurements were made at angles of attack from 0 deg to +/- 15 deg for control deflections from -60 deg to 60 deg. This report contains tabulated pressure data for the complete range of test conditions.
Document ID
19650023666
Acquisition Source
Legacy CDMS
Document Type
Other - NACA Research Memorandum
Authors
Lord, D. R. (National Advisory Committee for Aeronautics. Langley Aeronautical Lab. Langley Field, VA, United States)
Date Acquired
September 2, 2013
Publication Date
November 8, 1957
Subject Category
Aerodynamics
Report/Patent Number
NACA-RM-L57H30
Accession Number
65N33267
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
AERODYNAMICS
SWEPT WING
PRESSURE DISTRIBUTION
SUPERSONIC SPEED

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