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首页> 外文期刊>Journal of aerospace engineering >Computational Fluid Dynamics and Thermal Analysis to Estimate the Skin Temperature of Cockpit Surface in Various Flight Profiles
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Computational Fluid Dynamics and Thermal Analysis to Estimate the Skin Temperature of Cockpit Surface in Various Flight Profiles

机译：计算流体动力学和热分析，以估计各种飞行剖面中驾驶舱表面的表皮温度

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This paper discusses a simplified approach for estimation of skin temperature of aircraft at various flight conditions using computational fluid dynamics to aid precise estimation of cockpit heat load. Major heat load generated inside the cockpit is because of skin friction of air at high speeds. Hence, estimation of the stagnation temperature on aircraft skin is important. Accurate estimation of heat loads will enable the optimum design of air conditioning system with minimal weight and fuel penalty to improve endurance of aircraft. This paper gives a methodology for the calculation of skin temperature by carrying out three-dimensional (3D) modeling of the cockpit in computer aided design software, tetrahedral meshing and simulation in computational fluid dynamics (CFD) design software at various angles of attack (AoA), aircraft speed, and ambient temperatures using CFD software. The solver results are validated by comparing experimental results of Robinson and Hannemann's standard force reference model HB-2. This research has successfully generated variation of skin temperature at X, Y, and Z positions on external surface of cockpit at variable speed and angle of attack of aircraft along with governing equations of 2nd order polynomials. These governing equations will help the user to estimate skin temperature without rerunning simulation jobs in computational fluid dynamics design software. The results of a detailed analysis of the computational fluid dynamics design show that skin temperature under transient conditions at various angle of attack remains 0.9472 times the theoretical stagnation temperature with viscous heat dissipation.
机译：本文讨论了一种简化的方法，该方法利用计算流体力学来帮助估算座舱热负荷，从而在各种飞行条件下估算飞机的蒙皮温度。驾驶舱内部产生的主要热负荷是由于空气在高速下皮肤的摩擦。因此，估计飞机皮肤上的停滞温度很重要。准确估算热负荷将使空调系统的优化设计达到最小的重量和燃油消耗，从而提高飞机的耐久性。本文通过在计算机辅助设计软件中对驾驶舱进行三维（3D）建模，四面体网格划分以及在各种攻角（AoA）下的计算流体力学（CFD）设计软件中的仿真，提供了一种计算皮肤温度的方法。 ），飞机速度和环境温度（使用CFD软件）。通过比较Robinson和Hannemann的标准力参考模型HB-2的实验结果来验证求解器的结果。该研究成功地产生了飞机外罩在X，Y和Z位置的皮肤温度变化，该速度随飞机的速度和攻角的变化而变化，并伴随着二阶多项式的控制方程。这些控制方程式将帮助用户估计皮肤温度，而无需在计算流体动力学设计软件中重新运行模拟作业。对计算流体动力学设计进行详细分析的结果表明，瞬态条件下各种迎角下的皮肤温度仍然是理论滞止温度的0.9472倍，并具有粘性散热。

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