Steady and unsteady transonic flow
Steady and unsteady transonic flow
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DOI：
10.2514/6.1978-160
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发表时间：
1978
期刊：
影响因子：
--
通讯作者：
H. L. Seegmiller;J. Marvin;L. L. Levy-L.
中科院分区：
文献类型：
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作者：
H. L. Seegmiller;J. Marvin;L. L. Levy-L.
本文对跨音速圆弧翼型绕流进行了研究，以获得激波诱导分离流湍流模型的基本信息，并验证正在开发的模拟这种流动的数值计算程序。调查包括采用激光测速仪获得的数据有关的平均速度，剪切应力，和湍流动能剖面的翼型弦中段下游的流场的流动特征更复杂。取决于自由流马赫数，形成的流场要么是稳定的，激波诱导分离从激波根部延伸到后缘之外，要么是不稳定的，周期性运动也经历激波诱导分离。将实验数据与数值模拟结果进行了比较，数值模拟采用了求解时间相关的雷诺平均可压缩Navier-Stokes方程的计算机代码。
An investigation of the transonic flow over a circular arc airfoil was conducted to obtain basic information for turbulence modeling of shock-induced separated flows and to verify numerical computer codes which are being developed to simulate such flows. The investigation included the employment of a laser velocimeter to obtain data concerning the mean velocity, the shear stress, and the turbulent kinetic energy profiles in the flowfield downstream of the airfoil midchord where the flow features are more complex. Depending on the free-stream Mach number, the flowfield developed was either steady with shock-wave-induced separation extending from the foot of the shock wave to beyond the trailing edge or unsteady with a periodic motion also undergoing shock-induced separation. The experimental data were compared with the results of numerical simulations in which a computer code was employed that solved the time-dependent Reynolds' averaged compressible Navier-Stokes equations.