TRANSITION OF COMPRESSIBLE HIGH ENTHALPY BOUNDARY-LAYER FLOW OVER A FLAT-PLATE

This paper presents the results of an experimental investigation into the characteristics of boundary layer transition to turbulence in hype rvelocity air flows. A series of experiments was conducted using a fla t plate model, equipped with static pressure and thin film beat transf er transducers, in a free piston shock tunnel. Transition was observed in the stagnation enthalpy range of 2.35 to 19.2 MJ/kg. The transitio n Reynolds number correlates well with the unit Reynolds number throug h a simple empirical relation. The influences of Mach number, pressure and wall cooling are examined. The measured heat transfer rates in la minar and turbulent regions are compared with empirical predictions. F reestream disturbances of the test flow were also measured and analyse d.