AbstractThis 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.
Computational Fluid Dynamics and Thermal Analysis to Estimate the Skin Temperature of Cockpit Surface in Various Flight Profiles
Journal of aerospace engineering ; 28 , 1
2015
Article (Journal)
English
British Library Online Contents | 1996
|COCKPIT FLIGHT INSTRUMENT PANEL ARRANGEMENT
SAE Technical Papers | 1953