Analytical and experimental studies of shock interference heating in hypersonic flows
National Aeronautics and Space Administration, 1973 - Science - 137 pages
An analytical and experimental study is presented of the aerodynamic heating resulting from six types of shock interference patterns encountered in high speed flow. Centerline measurements of pressure and heat transfer distributions on basic bodies were obtained in four wind tunnels for Mach numbers from 6 to 20, specific heat ratios from 1.27 to 1.67, and free stream Reynolds numbers from 3 million to 25.6 million per meter. Peak heating and peak pressures up to 17 and 7.5 times stagnation values, respectively, were measured. In general, results obtained from semiempirical methods developed for each of the six types of interference agreed with the experimental peaks.
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0.025-m-diameter hemisphere body angle boundary layer Calculated laminar conditions in region configuration cylinder Experiment Calculated Experiment No interference fin at Mach flow conditions flow field flow models FLOW-VISUALIZATION DATA free-stream Mach number free-stream pitot pressure heat transfer heat-transfer amplification Heat-transfer distribution heat-transfer rate HEAT-TRANSFER TEST hemisphere at Mach interference Calculated peaks IV Epoxy jet bow shock jet impingement Kcyl Mach 6 air Mach reflection methods Model material N/cm NASA TN Nose peak heating peak pressure Pressure amplification pressure and heat pressure and heat-transfer Pressure distribution Pstag Pt oo Qstag reference values Reynolds numbers Schlieren photograph Shadowgraph shear layer attachment shock displacement length shock generator angle Shock Impingement shock interference heating shock interference patterns shock—boundary-layer interaction shown in figure specific heat ratio stag Test run stagnation point stagnation pressure stagnation-line surface TABLE Test run Pt Tetrafluoromethane Type IV interference Type IVa U.S. Air Force velocity gradient