The Reynolds number effect induced by model scaling and inflow conditions will affect the aerodynamic and starting characteristics of a two-dimensional hypersonic inlet. This effect is investigated through a numerical simulation method. First, the numerical simulation method is validated through experimental data. The static pressure from the numerical simulation method agreed well with wind tunnel tests. Then, this simulation method is used to study the Reynolds number effect on a two-dimensional hypersonic inlet caused by the model scaling and inflow conditions. The numerical simulation results indicate that as the Reynolds number decreases from 4.86 x 10(6) to 9.71 x 10(4) with model scaling increases from 1 to 1/50, the relative boundary layer thickness at the entrance of the inlet increases from 10.4 to 21.2; as the flight altitude increases from 25.5 km to 36.5 km, which causes the Reynolds number to decrease from 5.67 x 10(6) to 1.07 x 10(6), the relative boundary layer thickness at the entrance of the inlet increases from 9.8 to 13.2. Finally, the Reynolds number effect on the aerodynamics and starting characteristics caused by these two different factors are compared. The results show that the effect of scaling the model is similar to the effect of changing the altitude. As the relative boundary layer thickness increased by 1.0, the total pressure recovery at the throat section decreased by 0.8, and the inlet starting Mach number increased by 0.1.
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机译：模型缩放和流入条件引起的雷诺数效应将影响二维高超音速进气口的空气动力学和起始特性。通过数值模拟方法研究了这种效应。首先，通过实验数据验证了数值模拟方法的有效性;数值模拟方法的静压与风洞试验吻合较好。然后，利用仿真方法研究了模型缩放和流入条件对二维高超声速入口的雷诺数效应。数值模拟结果表明，随着模型比例从1增加到1/50，雷诺数从4.86 x 10（6）减小到9.71 x 10（4），入口处的相对边界层厚度从10.4%增加到21.2%;随着飞行高度从25.5 km增加到36.5 km，导致雷诺数从5.67 x 10（6）减小到1.07 x 10（6），入口处的相对边界层厚度从9.8%增加到13.2%。最后，比较了这两个不同因素对空气动力学和起动特性的雷诺数效应。结果表明，缩放模型的效果与改变海拔的效果相似。随着相对边界层厚度增加1.0%，喉部总压力回收率降低0.8%，入口起马赫数增加0.1。
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