AIAA Journal · 1968 · 219 citations · 5 references
EngineeringMechanical EngineeringPhysicsFluid DynamicsHeat TransferHeatingHeat Transfer In FluidsHeat Transfer ModelingHypersonic AerodynamicsShock ResponseShock WavesBlunt Body HeatingBow Shock DynamicsHeat Transfer MechanismsHeat Transfer RateHypersonic FlowJet ImpingementShock InteractionShock-wave Interaction
Shock impingement on a blunt body in hypersonic flow alters the surrounding flow and raises local heat‑transfer rates near the impingement point. The study develops a novel quasi‑static technique to investigate shock‑induced heat‑transfer enhancement on blunt bodies. The authors used a hemispherical glass model equipped with platinum thermometers, placed in a hypersonic tunnel through a slot in a variable‑incidence flat plate, and employed analog networks to map heat‑transfer rates while a physical model predicted shock interference patterns, pressure distributions, and peak‑heating characteristics. Heat‑transfer peaks up to ten times freestream values were observed, most intense on the side nearest the plate, growing with shock strength and confined to a narrow region where a shear layer or jet from the bow‑shock/impinging‑shock intersection contacts the surface. Nomenclature: M = Mach number, P = pressure normalized to freestream pressure, q = heat‑transfer rate (cal‑cm⁻²‑s⁻¹), r = radius of hemisphere (mm), t = time (s), T = temperature (°C), U = velocity normalized to freestream velocity, V = injection speed (m‑s⁻¹), x = distance along surface from stagnation point (mm).
An extraneous shock impinging on a blunt body in hypersonic flow is observed to alter the flow around the body and increase the local heat-transfer rate near the impingement point. A novel, quasi-static technique is developed to study this phenomenon. A hemispherical, glass model, equipped with platinum thin-film thermometers, is injected into a hypersonic tunnel through a slot in a variable-incidence flat plate. Analog networks provide graphs of the heat-transfer rates at various points on the model as a function of the model's position relative to the extraneous shock. Peaks in local heat-transfer rates up to 10 times the local, unperturbed, freestream values are recorded as the model traverses the shock. The peak heating is severest on the side of the model nearest the plate and increases with increasing shock strength, occurring over a narrow region where a shear layer or jet, originating at the intersection of the bow shock and the impinging shock, meets the model surface. A physical model is set up which predicts variations in shock interference patterns, in surface pressure distributions, and in the intensity and extent of the peak heating in accordance with experiment. Nomenclature M = Mach number P = pressure normalized with respect to freestream pressure q = heat-transfer rate, cal-cm~2-sec~1 r = radius of hemisphere, mm t = time, sec T = temperature, °C U = velocity normalized with respect to freestream velocity V = injection speed, m-sec1 x = distance along surface measured from stagnation point, mm
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