Abstract
College of Aeronautics* Cranfield Institute of Technology, UK This study provides a sound theoretical foundation for a well -established but heretof ore-empirical cri t eri on for incipient separation in moderateiyhypersonic shock/boundary i a yer interactions. It is based on an examination of the leading high Reynolds number approxima tion to trip1 e deck theory combined with its reformulation in terms of the Reference Temperature concept. The analysis further provides extensions giving the effects of both low supersonic Mach numbers and non-adiabatic wail temperatures on incipient separation. 6 = flow deflection angle '&= wall shear stress a = Moo3/&* , viscous mteractlon parameter Subscripts AdrAB= adiabatic wall conditions = body surface e = local inviscid flow conditions at edge of boundary layer i.~. = incipient separation 0 = stagnation value R E F = based on Reference Temperature w = wall surface conditions Su erscript A ( ) = non-dimensional version of ( )
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