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Supersonic Flow Past a Slender Delta Wing. An Experimental Investigation Covering the Incidence Range –5° ≤ α ≤ 50°
Published online by Cambridge University Press: 07 June 2016
Summary
A detailed survey of a delta wing of 70° sweep has been performed at M = 2.5. The measurements include upper- and lower-surface pressure distributions, schlieren photographs, vapour-screen photographs and surface oil-flow visualisation. The results have been compared with thin-shock-layer theory and various other predictions.
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- Copyright © Royal Aeronautical Society. 1976
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