The Downstream Influence Of Mass Transfer At The Nose Of A Slender Cone
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Report Number: WADD TR 60-892
Author(s): Cresci, Robert J., Libby, Paul A.
Corporate Author(s): Polytechnic Institute Of Brooklyn
Laboratory: Directorate of Materials and Processes
Date of Publication: 1961-05
Pages: 46
Contract: AF 33(616)-5944
DoD Project: 7364
DoD Task: 73652
Identifier: AD0257807
Abstract:
The influence of localized mass transfer at the nose of a slender cone under hypersonic flow conditions was studied by experimental and theoretical means. Two gaseous coolants, nitrogen and helium are injected through a porous plug subtending a half angle of 30°. The effect of the mass transfer on the shock shape, pressure distribution, heat transfer and transition are investigated. The experimental work involved tests in the Mach number 8.0 tunnel at PIBAL. The theoretical analysis involved a study of the effect of mass transfer on the shock stand-off distance and leads to an inviscid flow parameter permitting the experimentally determined shock shape and pressure distribution to be extrapolated to other than test conditions and to other coolant gases. There is obtained the maximum value of this parameter resulting in no significant alteration of the pressure distribution on the cone and thus defining the flows in which boundary layer type of similarity applies. Significant reductions in heat transfer are obtained with injection. Indeed with small amounts of helium injection the peak heating is found to occur downstream on the cone and to be an order of magnitude less than would occur at the stagnation point without mass transfer. With nitrogen early transition is found to occur so that local heating rates are actually increased over those prevailing at the same Reynolds number without injection.
Provenance: Lockheed Martin Missiles & Fire Control
Author(s): Cresci, Robert J., Libby, Paul A.
Corporate Author(s): Polytechnic Institute Of Brooklyn
Laboratory: Directorate of Materials and Processes
Date of Publication: 1961-05
Pages: 46
Contract: AF 33(616)-5944
DoD Project: 7364
DoD Task: 73652
Identifier: AD0257807
Abstract:
The influence of localized mass transfer at the nose of a slender cone under hypersonic flow conditions was studied by experimental and theoretical means. Two gaseous coolants, nitrogen and helium are injected through a porous plug subtending a half angle of 30°. The effect of the mass transfer on the shock shape, pressure distribution, heat transfer and transition are investigated. The experimental work involved tests in the Mach number 8.0 tunnel at PIBAL. The theoretical analysis involved a study of the effect of mass transfer on the shock stand-off distance and leads to an inviscid flow parameter permitting the experimentally determined shock shape and pressure distribution to be extrapolated to other than test conditions and to other coolant gases. There is obtained the maximum value of this parameter resulting in no significant alteration of the pressure distribution on the cone and thus defining the flows in which boundary layer type of similarity applies. Significant reductions in heat transfer are obtained with injection. Indeed with small amounts of helium injection the peak heating is found to occur downstream on the cone and to be an order of magnitude less than would occur at the stagnation point without mass transfer. With nitrogen early transition is found to occur so that local heating rates are actually increased over those prevailing at the same Reynolds number without injection.
Provenance: Lockheed Martin Missiles & Fire Control