تحلیل آیرودینامیکی یک کپسول بازگشت به جو با در نظرگرفتن انتقال حرارت تشعشعی

In design of high speed projectiles, aerodynamic and heating analysis has an important role. For capsules, Which enter the Earth's atmosphere, approximately, radiation heat flux is 10 to 40 percent of total heat flux.‌‌ Therefore, If radiation heat flux of hypersonic flow calculations is not included in results, there will be a large error in calculations. In this research, the three-dimensional hypersonic ideal gas flow at Mach numbers 30 and 32.8 is studied. Discrete ordinates radiation model has been used for simulating radiation heat transfer and The effects of air and wall absorption coefficients,Wavelength and Refractive index are also considered in the simulation. Finally, Numerical simulation shows that,when the radiation model is active, temperature decreases 27 percent and pressure decreases 2 percent,too.So,pressure far field boundary Condition should be used to design cooling system and If cooling system for wall is not concluded in results, there will be a large error in calculations.

تحلیل آیرودینامیکی یک کپسول بازگشت به جو با در نظرگرفتن انتقال حرارت تشعشعی Keywords:

انتقال حرارت تشعشعی , ضریب جذب , طول موج , کپسول , ماورای صوت