스파이크가 부착된 유도탄의 공력 가열 해석 = Aerodynamic Heating Analysis of Spike-Nosed Missile

다국어 초록 (Multilingual Abstract)

Numerical analysis of aerodynamic heating for KPSAM is performed using aerodynamic heating model suitable to KPSAM, which has complex flow field resulting from the spike attached to the dome, such as large separation area and the strong shock/boundary layer interaction region around reattachment point on the dome. The aerodynamic heating model is validated and modified through the comparison between the flight test measurement and the thermal analysis results. TFD temperature sensors are installed on the dome to measure surface temperature during the flight. Computation results, obtained from the heat transfer analysis on the sensors, agree well with flight test data. The aerodynamic heating model provides heat transfer rate into surface as a boundary condition of unsteady 1D/axisymmetric thermal analysis on the missile structure. The axisymmetric thermal analysis using FLUENT is more versatile than the 1D analysis and can be applied to the heating problem related with complex structures and multi-dimensional heat transfer problems such as prediction of temperature rise at contact surface of different materials.

참고문헌 (Reference)

1 정석영, "“신궁유도탄의 공력 가열 해석 ”" 국방과학연구소 2001

2 Hayes, "“Introduction to the Aerodynamic Heating Analysis of Supersonic Missiles” Progress in Astronautics and Aeronautics" 1991

3 Poll, "“An Introduction to the Problem of Aerodynamic Heating”"

4 Chang, "Separation of Flow" 1979

5 윤성준, "PSAM 공력특성 분석" 국방과학연구소 1997

6 and Bradshaw, "Momentum Transfer in Boundary Layers" Hemisphere Publishing Corporation and McGraw-Hill Book Company 1977

7 Truitt, "Fundamentals of Aerodynamic Heating" The Ronald Press Company 1960

8 Schlichting, "Boundary Layer Theory translated by Kestin" McGraw- Hill Book Company 1985