| Autor: |
Bhatkar, Vijay W., Shete, Ganesh V., Allampallewar, Girish L., Patil, Bhuvaneshwar D., Mutalikdesai, Sachin V., Shastri, Dhiresh S. |
| Předmět: |
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| Zdroj: |
International Journal of Vehicle Structures & Systems (IJVSS); 2024, Vol. 16 Issue 2, p235-241, 7p |
| Abstrakt: |
Hypersonic flight is of extreme interest today because of a new vehicle concept designed to fly at very high Mach numbers. In hypersonic flows, strong shocks are generated with a thicker boundary layer around the surface of flights. In hypersonic flows, nose bluntness for the leading edges of the aerofoil is extremely useful for maximum lift to drag ratio to reduce aerodynamic heating. In hypersonic flows, space between the blunt body nose and the shock generated is mixed subsonic and supersonic flow through the sonic line. The only CFD method available today is the time marching method, as the unsteady equations of motion are hyperbolic with respect to time regardless of whether the flow is locally subsonic or supersonic. ANSYS ICEM CFD is used for meshing two and three-dimensional models as it is having a powerful blocking method. Fluent was used as a solver and postprocessor. A computational study of flow around a power law body was conducted for a Mach number of 8.2, pressure = 951.5 N/m2, temperature = 89.3 K and velocity = 1553 m/s. The Mach number contours obtained were close to experimental values. Coefficient of Drag (CD), Coefficient of Lift (CL) and Coefficient of Moment (CM) obtained were matching to the experimental results. [ABSTRACT FROM AUTHOR] |
| Databáze: |
Complementary Index |
| Externí odkaz: |
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