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Aerodynamic characteristics of wings designed with a combined-theory method to cruise at a Mach number of 4.5A wind-tunnel study was conducted to determine the capability of a method combining linear theory and shock-expansion theory to design optimum camber surfaces for wings that will fly at high-supersonic/low-hypersonic speeds. Three force models (a flat-plate reference wing and two cambered and twisted wings) were used to obtain aerodynamic lift, drag, and pitching-moment data. A fourth pressure-orifice model was used to obtain surface-pressure data. All four wing models had the same planform, airfoil section, and centerbody area distribution. The design Mach number was 4.5, but data were also obtained at Mach numbers of 3.5 and 4.0. Results of these tests indicated that the use of airfoil thickness as a theoretical optimum, camber-surface design constraint did not improve the aerodynamic efficiency or performance of a wing as compared with a wing that was designed with a zero-thickness airfoil (linear-theory) constraint.
Document ID
19880010036
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Mack, Robert J. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 5, 2013
Publication Date
April 1, 1988
Subject Category
Aerodynamics
Report/Patent Number
NAS 1.60:2799
L-16333
NASA-TP-2799
Accession Number
88N19420
Funding Number(s)
PROJECT: RTOP 505-62-81-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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