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首页> 外文会议>Eighth International Conference on Computational Fluid Dynamics >Numerical Simulation of Transition Effects in Hypersonic Flow around a Double Wedge Using a Correlation-Based Intermittency Model
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Numerical Simulation of Transition Effects in Hypersonic Flow around a Double Wedge Using a Correlation-Based Intermittency Model

机译：基于相关性的间歇模型对双楔绕高超声速流动过渡效应的数值模拟

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摘要

To study the engine inlet transition flow for an air breathing hypersonicrnvehicle, a typical model of a double wedge is chosen and the correlation-basedrnintermittency model is applied in this paper. Based on the tunnel experimentsrncarried by Neuenhahn.Thomas from Aachen university in Germany, the calculationrnresults are discussed. The results obtained under the condition of laminar flowrncalculation can not be in respond to the flow character in the tunnel experiments.rnAnd the results obtained in full turbulent cases can not be in respond to those too.rnOnly the numerical simulations carried out considering the transition mechanismrnaccord with the tunnel experiments. In the paper the results obtianed from thernsimulation only using the combined method of MUSCL, SST model, -Re modelrncan accord with the experiment data and reproduce rightly the state of the tunnelrnexperiment.Firstly, the γ-Re_θ model by Langtry/Menter using in this paper should be introduced briefly. The intermittency equation and the transport equation of transition onset momentum thickness Reynolds number are formulated as follows:(δ)(ργ)/(δt)+(δ)(ρU_jγ)/(δ)x_j=P_r-E_r+(δ)/(δ)x_j[(μ+μ_t/σ_f)(δ)γ/(δ)x_j]rn(δ)(ρRe_(θt))/(δ)t+(δ)(ρU_jRe_(θt))/(δ)x_j=P_(θt)+(δ)/(δ)x_j[σ_(θt)(μ+μ_t)(δ)Re_(θt)/(δ)x_j)].Secondly, the sketch of double wedge is shown :In the calculation the mach number is 8.3, the Reynolds number is 3.76e+6/m, thernwall temperature is set 300K and 600K respectively, and leading edge bluntness isrninvestigated. The freestream turbulence intensity 0.5% is chosen.rnIn fig 2 and fig 3 the calculation results show that, under the different wallrntemperatures the transition flow all occurs around the corner, the separated flowrnexists and it's size increases with wall temperature rising.Only considering a single wedge model by extending the first ramp length to 4m,rnunder the similar condition of calculation, the position of transition onset arerndifferent from that in the double wedge model. In the simulation of the singlernwedge models the position of transition onset moves downstream along with thernleading edge bluntness increasing. In the case of the sharp leading edge model thernposition of transition onset is at about 1.6m. But in the case of the 1mm leadingrnedge model the position of transition onset is at about 2.6m.
机译：为了研究超音速呼吸汽车的发动机进气过渡流，选择了典型的双楔形模型，并采用了基于相关的间歇性模型。以德国纽伦汉大学的隧道试验为基础，讨论了计算结果。在层流计算条件下获得的结果不能响应隧道实验中的流动特性。而且在全湍流情况下获得的结果也不能响应这些结果。rn仅在考虑过渡机理的情况下进行了数值模拟与隧道实验。本文仅将MUSCL，SST模型，-Re模型的组合方法从模拟中得出的结果与实验数据相吻合，并正确再现了隧道实验的状态。首先，Langtry /的theγ-Re_θ模型本文将简要介绍使用方法。过渡开始动量厚度雷诺数的间断方程和输运方程公式如下：（δ）（ργ）/（δt）+（δ）（ρU_jγ）/（δ）x_j = P_r-E_r +（δ）/（ δ）x_j [（μ+μ_t/σ_f）（δ）γ/（δ）x_j] rn（δ）（ρRe_（θt））/（δ）t +（δ）（ρU_jRe_（θt））/（δ）x_j = P_（θt）+（δ）/（δ）x_j [σ_（θt）（μ+μ_t）（δ）Re_（θt）/（δ）x_j）]。第二，显示双楔形的草图：计算马赫数为8.3，雷诺数为3.76e + 6 / m，壁温分别设置为300K和600K，并研究了前沿钝性。选择的自由流湍流强度为0.5％。在图2和图3中，计算结果表明，在不同壁温下，过渡流都在拐角处发生，分离的流存在，并且其大小随壁温的升高而增加，仅考虑单个在相似的计算条件下，通过将第一坡道长度扩展到4m来建立楔形模型，过渡起始位置与双楔形模型中的过渡起始位置不同。在单楔模型的仿真中，过渡过渡的位置随着前缘钝度的增加而向下游移动。在锋利的前缘模型的情况下，过渡开始的位置大约为1.6m。但是对于1mm的前缘模型，过渡开始位置大约为2.6m。

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