ENTHALPY EFFECTS ON HYPERVELOCITY BOUNDARY-LAYER TRANSITION : GROUND TEST AND FLIGHT DATA

Boundary-layer-transitionexperiments on a 5-deg half-anglecone at 0-deg angle of attackwere performed in the T5 hypervelocity shock tunnel. The test gases investigated included air, nitrogen, and carbon dioxide. Reservoir enthalpies were varied from 3 to 27MJ/kg and reservoir pressures from 10 to 95MPa, depending on the gas and tunnel settings. No clear relationship is found to exist between the transition Reynolds number based on the boundary-layer-edge conditions and the reservoir enthalpy. However, when the reference temperature conditions are used instead, the different test gases are distinguishable and ordered according to their dissociation energy. Data from a free- ight experiment are also compared with the shock tunnel experiments. When the transition Reynolds numbers are evaluated at the boundary-layer-edge conditions, they are an order of magnitude higher than the tunnel results. However, when the reference conditions are used, the  ight data fall within the same range as the experiments, although the trend with reservoir enthalpy is reversed.

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