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Tabulated Data From a Pressure-Distribution Investigation at Mach Number 2.01 of a 45 Deg Sweptback-Wing Airplane Model at Combined Angles of Attack and SideslipA pressure-distribution investigation of a wing-body combination has been conducted in the Langley 4- by 4-foot supersonic pressure tunnel at a Mach number of 2.01. The model configuration consisted of an ogive-circular-cylinder body (fineness ratio of approximately ii) and a wing with 45 deg of sweepback at the quarter-chord line, an aspect ratio of 4, and a taper ratio of 0.2. Data were obtained on high-, mid-, and low-wing configurations and for the body and wing alone for a range of angles of attack and yaw from 0 deg to 15 deg. The tabulated pressure coefficients are presented in this report.
Document ID
19630002621
Acquisition Source
Langley Research Center
Document Type
Other - NASA Memorandum (MEMO)
Authors
Gapcynski, John P. (NASA Langley Research Center Hampton, VA, United States)
Landrum, Emma Jean (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 2, 2013
Publication Date
November 1, 1958
Subject Category
Aerodynamics
Report/Patent Number
NASA-MEMO-10-15-58L
Accession Number
63N12497
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
PRESSURE DISTRIBUTION
SUPERSONIC FLOW
SWEPTBACK WING

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