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Boundary Layer Transition Measurements Using a Surface Hot Film Downstream of Distributed Roughness at Mach Numbers from 1·3 to 4·0
Published online by Cambridge University Press: 04 July 2016
Summary
A surface hot film was used as a boundary layer transition indicator on wind tunnel models at Ifiach numbers from 1·3 to 4·0. The results illustrate the difficulty of fixing transition with distributed roughness on small models at supersonic speeds.
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- Copyright © Royal Aeronautical Society 1965
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