Extension and application of a scaling technique for duplication of in-flight aerodynamic heat flux in ground test facilities
conference paper
To enable direct experimental duplication of the inflight heat flux distribution on supersonic and hypersonic vehicles, an aerodynamic heating scaling technique has been developed. The scaling technique is based on the analytical equations for convective heat transfer for laminar and turbulent boundary layers that follow from applying the Reynolds analogy. The method was developed starting from an elementary isothermal cold flat plate at zero angle of attack and subsequent introduction of wall temperature effects, geometrical scaling effects and angle of attack effects. The present paper extends the scaling technique by introducing correction factors enabling full duplication of the laminar and turbulent boundary layer heat transfer downstream of a shock wave generated by a flat plate at angle of attack. A similar extension is developed to enable full duplication of the laminar and turbulent boundary layer heat transfer downstream of a Prandt- Meyer expansion. The scaling technique is applied to a simplified vehicle configuration consisting of two convex surfaces. The results clearly show that scaled test conditions can be derived at which the in-flight distribution of heat flux on either one of the two surfaces can be fully duplicated. After implementation of high temperature effects this scaling technique may allow for experimental verification of the heat flux distribution on hypersonic vehicles at supersonic test conditions. In this way, test facilities that are far less expensive to operate can provide valuable information during the initial design phase of a hypersonic vehicle.
Topics
Cold flat plateConvective heat transferConvex surfacesCorrection factorsExperimental verificationFlight aerodynamicsGeometrical scalingGround test facilitiesHeat flux distributionsHypersonic vehiclesReynolds analogySupersonic and hypersonicTurbulent boundary layersVehicle configurationWall temperaturesAngle of attackBoundary layer flowGas dynamicsHeat exchangersHypersonic aerodynamicsIon beamsTest facilitiesThermal effectsTurbulent flowUltrasonic testingAircraft instruments
TNO Identifier
241601
ISSN
0379-6566
ISBN
9789292212230
Source title
6th European Symposium on Aerothermodynamics for Space Vehicles, Versailles, France, 3–6 November 2008 (ESA SP-659, January 2009)
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