نویسندگان
1 پژوهشگاه هوافضا، وزارت علوم، تحقیقات و فناوری، تهران، ایران
2 دانشکدة مهندسی هوافضا، دانشگاه صنعتی شریف، تهران، ایران
چکیده
An accurate and efficient computational procedure is developed to predict the laminar hypersonic flowfield for both the perfect gas and equilibrium air around the axisymmetric blunt body configurations. To produce this procedure, the boundary layer equations utilize the integral matrix solution algorithm for the blunt nose and after body region by using a space marching technique. The integral matrix procedure enables us to create accurate and smooth results using the minimum grid in the boundary layer and to minimize the computational costs. This algorithm is highly appropriate for the design of hypersonic reentry vehicles. The effects of real gas on the flowfield characteristics are also studied in boundary layer solutions. Comparisons of the results with experimental data demonstrate that accurate solutions are obtained.
کلیدواژهها
عنوان مقاله [English]
Equilibrium Effects on the Hypersonic Laminar Boundary Layer Flow over Axisymmetric Bodies
نویسندگان [English]
- Ramin Kamali Moghadam 1
- Mohammad Reza Salimi 2
1 Aerospace Research Institute, Ministry of Science, Research and Technology, Tehran, Iran
2 Aerospace Engineering Department, Sharif University of Technology.Tehran.IRAN
چکیده [English]
An accurate and efficient computational procedure is developed to predict the laminar hypersonic flowfield for both the perfect gas and equilibrium air around the axisymmetric blunt body configurations. To produce this procedure, the boundary layer equations utilize the integral matrix solution algorithm for the blunt nose and after body region by using a space marching technique. The integral matrix procedure enables us to create accurate and smooth results using the minimum grid in the boundary layer and to minimize the computational costs. This algorithm is highly appropriate for the design of hypersonic reentry vehicles. The effects of real gas on the flowfield characteristics are also studied in boundary layer solutions. Comparisons of the results with experimental data demonstrate that accurate solutions are obtained.
کلیدواژهها [English]
- Hypersonic Flow
- Equilibrium air
- Boundary Layer
- Integral matrix method