- Volume 30 Issue 6
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Quasi-Transient Method for Thermal Response of Blunt Body in a Supersonic Flow
준-비정상해석 기법을 통한 초음속 유동 내 무딘 물체의 열응답 예측
- Bae, Hyung Mo (Department of Mechanical Engineering, Yonsei Univ.) ;
- Kim, Jihyuk (Department of Mechanical Engineering, Yonsei Univ.) ;
- Bae, Ji-Yeul (Department of Mechanical Engineering, Yonsei Univ.) ;
- Jung, Daeyoon (Agency for Defense Development) ;
- Cho, Hyung Hee (Department of Mechanical Engineering, Yonsei Univ.)
- Received : 2017.10.27
- Accepted : 2017.11.21
- Published : 2017.12.29
In the boundary layer of supersonic or hypersonic vehicles, there is the conversion from kinetic energy to thermal energy, called aerodynamic heating. Aerodynamic heating has to be considered to design supersonic vehicles, because it induces severe heat flux to surface. Transient heat transfer analysis with CFD is used to predict thermal response of vehicles, however transient heat transfer analysis needs excessive computing powers. Loosely coupled method is widely used for evaluating thermal response, however it needs to be revised for overestimated heat flux. In this research, quasi-transient method, which is combined loosely coupled method and conjugate heat transfer analysis, is proposed for evaluating thermal response with efficiency and reliability. Defining reference time of splitting flight scenario for transient simulation is important on accuracy of quasi-transient method, however there is no algorithm to determine. Therefore the research suggests the algorithm with various flow conditions to define reference time. Supersonic flow field of blunt body with constant acceleration is calculated to evaluate quasi-transient method. Temperature difference between transient and quasi-transient method is about 11.4%, and calculation time reduces 28 times for using quasi-transient method.
Supported by : 국방과학연구소
- Anderson, J.D. (2000) Hypersonic and High Temperature Gas Gynamics, AIAA, p.696.
- Hayashi, K., Aso, S., Tani, Y. (2006) Experimental Study on Thermal Protection System by Opposing Jet in Supersonic Flow, J. Spacecr. & Rocket., 43(1), pp.233-235. https://doi.org/10.2514/1.15332
- Hayashi, K., Aso, S., Tani, Y. (2006) Numerical Study on Aerodynamic Heating Reduction by Opposing Jet, Department of Aeronautics and Astronautics, Faculty of Engineering, Kyushu University.
- Menter, F.R. (2009) Review of the Shear-Stress Transport Turbulence Model Experience from an Industrial Perspective, Int. J. Comput. Fluid Dyn., 23(4), pp.305-316. https://doi.org/10.1080/10618560902773387
- Zhang, S., Chen, F., Liu, H. (2014) Time-Adaptive, Loosely Coupled Strategy for Conjugate Heat Transfer Problems in Hypersonic Flows, J. Thermophys. & Heat Transf., 28(4), pp.635-646. https://doi.org/10.2514/1.T4278