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Numerical Calculation Aerodynamic Heating over Projectiles’ Head at Hypersonic Flow

Author: ZhangJunBo
Tutor: ZhangMin
School: Nanjing University of Technology and Engineering
Course: Fluid Mechanics
Keywords: Hypersonic Aerothermal Unstructured grid Finite volume method
CLC: TJ410.2
Type: Master's thesis
Year: 2009
Downloads: 321
Quote: 3
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Abstract


Hypersonic flight in the dense layers of the atmosphere MISSILES ( Mach number Ma = 5 to 8 ) , approximate calculations and numerical simulation combined approach , calculated analysis of Shell Head aerodynamic heating and the internal temperature field distribution . For of blunt head spin into the body of a laminar boundary layer heating , fee - Riddle (Fay-Riddle) equilibrium boundary layer stagnation point heat flux density formula head stagnation point heat flux , then Lees methods to heat flux Shell Head stagnation point heat flux density normalized representation . The numerical discrete time , into the heat flux formula linear function of the wall temperature relationship , and as a bomb arrows , temperature field numerical simulation of boundary conditions . Bombs inside , using the finite volume method , second order accuracy, fully implicit discrete three-dimensional unsteady heat conduction equation in unstructured grid . Due to the non-orthogonal grid and high accuracy requirements , while alternately calculated diffusion ( normal component ) and the second diffusion ( tangential component ) . The Fortran95 language programming using modular completed the preparation of the two-dimensional and three-dimensional program ; and achieve grid before processing the multi-functional direct docking with the generic commercial software Tecplot and Gambit . Finally , to fully verify the correctness of the program after the thermal environment engineering algorithms and numerical simulation of the temperature field coupled to two different warheads model for the numerical simulation of the temperature field in the Shell Head , the distribution of the maximum temperature range and dynamic temperature field changes in the law . The results show that : the Mach number , the head ball head diameter is an important factor affecting the aerodynamic heating . The results of this paper is correct , credible and has some practical value , the reference for the engineering design .

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