Heat Transfer Boundary Condition Calculation Model of a Fighter Plane Cockpit / 航天医学与医学工程

ABSTRACT

Objective To establish a complete heat transfer boundary condition model in a cockpit including the inner wall heat transfer boundary condition and the air supply heat transfer boundary condition of the air distribution system. Methods The temperature field in the cockpit was carried out unmerical caculation with above model and the traditional method which was assumed uniform heat flux through walls and flow flux out of each air supply hole individually.An experiment was carried out to prove the caculation accuracy of both methods. Results The comparison between calculation and experiment results shows that the temperature field calculation accuracy of this model was much higher than traditional method’s.This model could indicate the unevenness and the asymmetry of the heat transfer through walls and the air temperature out of air supply holes of air distribution system. Conclusion This model is reasonable and has a good engineering application value.