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Numerical prediction of compressible heat flow with complex wall temperature in supersonic rocket nozzles

Wall heat transfer coefficients and static wall pressures are determined over wide ranges of stagnation pressures and stagnation temperatures under large pressure gradients in a cooled convergent-divergent nozzle. The effects of specific heat ratio, turbulent Prandtl number and wall temperature value on the heat transfer and on the position of separation flow are not yet discussed accurately. Computing correct boundary layer under adverse pressures gradients is of a particular importance to the accurate modeling of separated flow. This numerical investigation is conducted to assess the accuracy of the SST-V turbulence model when computing boundary layer separation in supersonic nozzle with heat transfer. It is concluded that the wall heat transfer coefficients and the position of separation point are influenced by the variation of many parameters as heat specific ratio, wall temperature and turbulent Prandtl number.
PAPER REVISED: 2016-09-25
PAPER ACCEPTED: 2016-09-28
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