CAJ | 학술논문

将基于流场当地变量的γ-Reθ转捩模型加入可压缩 RANS 方程计算程序，对平均流场控制方程、湍流和转捩控制方程进行基于 LU-SGS 的隐式紧耦合求解。结合三种压缩性修正方法对高超声速平板、双楔和圆锥流动进行了数值模拟，给出了壁面斯坦顿数、热流值和实验值的比较，以及湍动能和间歇因子分布云图。数值计算结果表明，相同来流湍流度下不同压缩性修正方法得到的转捩位置差别较大。相比于未修正的模型，基于当地马赫数压缩性修正后的转捩位置最靠后，其对带有分离的双楔流动预测较为准确；基于来流马赫数的压缩性修正仅使得转捩位置稍有延迟；对湍动能源项的压缩性修正可提高模型在转捩后湍流段的热流预测精度。
장기우류장당지변량적γ-Reθ전렬모형가입가압축 RANS 방정계산정서，대평균류장공제방정、단류화전렬공제방정진행기우 LU-SGS 적은식긴우합구해。결합삼충압축성수정방법대고초성속평판、쌍설화원추류동진행료수치모의，급출료벽면사탄돈수、열류치화실험치적비교，이급단동능화간헐인자분포운도。수치계산결과표명，상동래류단류도하불동압축성수정방법득도적전렬위치차별교대。상비우미수정적모형，기우당지마혁수압축성수정후적전렬위치최고후，기대대유분리적쌍설류동예측교위준학；기우래류마혁수적압축성수정부사득전렬위치초유연지；대단동능원항적압축성수정가제고모형재전렬후단류단적열류예측정도。
Boundary layer transition plays a significant role in the prediction of aerodynamic and aerothermodynamics characteristics of hypersonic vehicle.The commonly used correlation based onγ-Reθ transition model is implemented into a Reynolds-Averaged Navier-Stokes solver in order to evaluate its capability in hypersonic flows.The mean flow and turbulent flow equations are solved simultaneously based on the LU-SGS method.Three compressibility correction meth-ods are adopted to simulate the hypersonic flows around a flat plate,a double wedge and a cone body.Results of Stanton number,heat flux on walls,contours of turbulence kinetic energy and intermittency factor are presented.The results ofγ-Reθ transition model show better flow essen-tial than that of full laminar or full turbulent results.The transition onset positions obtained by different compressibility methods under the same free stream turbulence intensity varied signifi-cantly.Compressibility correction based on local Mach number delays the transition onset great-ly,while the correction of source term of turbulent kinetic energy equation improves the accuracy of heat flux on turbulent section of the wall.Rational selection of compressibility correction method should rely on the type of flow.Elaborate and reliable compressibility correction method still need to be further investigated.