원문정보
초록
영어
Aerodynamic coefficients of a reentry bodyin hypersonic flowfiled are calculated by using a three-dimensional flow solver. The high temperature real gas effects, thermal excitations and chemical reactions of air, are accounted for in the calculation. The reasonable agreement between the calculated aerodynamic coefficients and the Apollo AS-202 flight date are obtained. The effects of thermochemical nonequilibrium on the aerodynamic predictions are shown to be non-negligible.
목차
Abstract
1. Introduction
2. Method of calculations
2.1 Governing Equations
2.2 Thermochemical models
2.3 Transport properties
2.4 Numerical methods
3. Test Conditions
4. Results and Discussions
5. Summary
Acknowledgements
References
1. Introduction
2. Method of calculations
2.1 Governing Equations
2.2 Thermochemical models
2.3 Transport properties
2.4 Numerical methods
3. Test Conditions
4. Results and Discussions
5. Summary
Acknowledgements
References
저자정보
참고문헌
자료제공 : 네이버학술정보