1976•NASA STI Repository (National Aeronautics and Space Administration)Requires access
Supersonic pressure measurements and comparison of theory to experiment for an arrow-wing configuration
M. E. Manro
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Abstract
A wind tunnel test of an arrow-wing-body configuration consisting of flat and twisted wings, as well as leading- and trailing-edge control surface deflections, was conducted at Mach numbers from 1.54 to 2.50 to provide an experimental pressure data base for comparison with theoretical methods. Theory-to-experiment comparisons of detailed pressure distributions were made using a state-of-the-art inviscid flow, constant-pressure-panel method. Emphasis was on conditions under which this theory is valid for both flat and twisted wings.