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

Abstract

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.

Review Study on Thermal Characteristics of Bell Nozzle used in Supersonic Engine

“…al (2018) analyzed that axisymmetric nozzle flows with MacCormack's technique, a parallel implicit finite volume algorithm based on the entire Navier-Stokes unsteady equations is developed. The effects of various parameters on the thermal and dynamic properties of flow via a cooled convergent-divergent nozzle are discussed in the current results [32]. Akib et.al (2019) The density gradient is determined using the shadowgraph imaging method.…”

“…This study focuses on transition DBN aspects including transition persistence such as buffeting and flip-flopping, and sneak transition intervals, which are inherited properties of DBN stepped design [31]. Bensayah et. al (2018) analyzed that axisymmetric nozzle flows with MacCormack's technique, a parallel implicit finite volume algorithm based on the entire Navier-Stokes unsteady equations is developed.…”