University of North Texas Digital Library (University of North Texas) · 1954 · 59 citations · 0 references
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EngineeringAerospace EngineeringMechanical EngineeringAerodynamicsFluid DynamicsHeat TransferHeat FlowHeat Transfer AnalysisHeat Transfer FundamentalsHeat Transfer In FluidsHeat Transfer ModelingHeat Transfer CharacterizationHeat Transfer MechanismsIn-cylinder Heat TransferMach NumberMach Number EffectsPressure Coefficient DistributionReynolds NumberSupersonic Flow
Average heat-transfer, temperature-recovery, and pressure-distribution measurements were obtained over the hemispherical nose of a body of revolution both with and without flow-separation spikes. The tests, conducted in a range of Reynolds numbers from 1.55 to 9.85 x 10(5) and from Mach number 0.12 to 5.04, indicated that in supersonic flow the addition of spikes approximately doubles the rate of heat transfer, regardless of spike length.