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About the 'Camel Effect' on Heat Transfer to a Sphere at Hypersonic Flow Conditions

机译：关于高超声速流动条件下传给球体的“骆驼效应”

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This contribution investigates theoretically and experimentally the behavior of the heat fluxes on a sphere of 100 mm diameter at a flight Mach number 10 and atmospheric conditions as in 20 up to 70 km altitude. The theoretical calculations were performed with the TAU code of DLR, the German Aerospace Center. The turbulence was numerically modeled with the Spalart-Almaras-Original model (SAO) as well as with the k-ω model of Wilcox. Experiments are carried out with shock tunnel STB of ISL. Only at altitudes of 60 and 70 km, the simulation provides approximately the same heat flux distributions as measured. With decreasing altitude a remarkable effect occurs, referred herein as the "camel effect" with a maximum heat flux by side of the stagnation point. This "camel effect" increases with decreasing altitude which leads more and more to a broadened heat flux distribution in the front region of the sphere. At these lower altitudes the numerics differ markedly from the experiments. The reasons for the discrepancy between simulation and experiment is not clear yet, especially the "camel effect" is described imprecise by the numerics. Assuming that the measurements were made correctly within an error by ±10 percent, for the differences the turbulence modeling and/or the mesh refinement must be taken into consideration at the extreme boundary conditions at M_∞ = 10.
机译：该贡献从理论上和实验上研究了在飞行速度为10马赫数和20到70 km高度的大气条件下，直径为100 mm的球体上的热通量的行为。理论计算是使用德国航空航天中心DLR的TAU代码进行的。用Spalart-Almaras-Original模型（SAO）以及Wilcox的k-ω模型对湍流进行了数值建模。实验是用ISL的冲击隧道STB进行的。仅在60和70 km的高度上，该模拟才能提供与所测量的大致相同的热通量分布。随着海拔的降低，出现了显着的影响，在本文中称为“骆驼效应”，在停滞点附近具有最大的热通量。这种“骆驼效应”随着高度的降低而增加，这越来越导致球体前部区域的热通量分布变宽。在这些较低的海拔高度，数值与实验明显不同。目前尚不清楚模拟与实验之间存在差异的原因，尤其是用数字不精确地描述了“骆驼效应”。假设正确地在±10％的误差范围内进行了测量，对于这些差异，必须在极端边界条件（M_∞= 10）下考虑湍流建模和/或网格细化。

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