Aerodynamic Heating Analysis of Supersonic Missile Body and Fin

Kang, Kyoung-Tai

Journal of the Korea Institute of Military Science and Technology 2008;11(4):20-28.

Kyoung-Tai Kang

초음속 유도탄 동체와 날개의 공력가열 해석

강경태

국방과학연구소

Abstract

Missile operating at supersonic conditions experiences considerable high temperature environments that is caused by aerodynamic heating as a result of the temperature gradient through boundary layer that surrounds it. This is one of important problems to the designer due to temperature limitation of structural materials. Because prediction of aerodynamic heating on missile needs unsteady calculation according to a flight trajectory, approximate method approach is efficient at design stage. In this paper, improved aerodynamic heating analysis scheme is introduced, which calculates heat flow and temperature by simple pressure field prediction on a missile body and fin. The prediction results are compared with measured data and MINIVER codes results.

Key Words: Aerodynamic Heating, Temperature Distribution, Supersonic Boundary Layer, Heat Transfer Coefficients, Supersonic Missile