Numerical Investigations of Local Correlation-Based Transition Model in Hypersonic Flows

Abstract

Numerical simulations of hypersonic flows using local correlation based transition (LCTM) model was performed in order to assess the accuracy of the model in hypersonic conditions. Implementation of the model was done in object oriented framework. The governing equations as well as the numerical methods are described. A series of runs were performed for simulating Mach 8 flow over a 7 o half angle sharp cone, using three different free stream turbulence intensity levels. Moreover, both Laminar and fully turbulent cases were also considered. The LCTM model behaves pretty well and the heat flux remain bounded between laminar and fully turbulent case. The model shows strong sensitivity to the free stream turbulence intensity level regarding the transition location. The results were compared with Kimmel 's experimental data and good agreement was obtained with 1% free stream turbulence intensity level.

Constrained large-eddy simulation of laminar-turbulent transition in compressible channel flows

“…Krause, Behr and Ballmann [18] constructed a relationship between F length and Re θ c by considering freestream turbulence intensities, allowing the simulation results to agree well with the experimental data in the cases of hypersonic double ramp. Bensassi, Lani and Rambaud [19] tested the model by simulating a Mach 8 flow over a 7 • half angle sharp cone at three different freestream turbulence intensity levels, where they reported that the heat flux in the transition regime shows excellent agreement with experimental data. Zhang et al [20,21] calibrated the basic γ − Re θ empirical correlation with different samples and results in different cases are satisfactory.…”

Constrained large-eddy simulation of laminar-turbulent transition in compressible channel flow

“…Krause and Behr [18] constructed a relationship between F length and Re θc by considering freestream turbulence intensities, allowing the simulation results to agree well with the experimental data in the cases of hypersonic double ramp. Bensassi, Lani and Rambaud [19] tested the model by simulating a Mach 8 flow over a 7 • half angle sharp cone at three different freestream turbulence intensity levels, where they reported that the heat flux in the transition regime shows excellent agreement with experimental data. Zhang et al [20,21] calibrated the basic γ − Re θ empirical correlation with different samples and results in different cases are satisfactory.…”