Numerical Simulation of Hypersonic Flow Over a Blunt Leading Edge Delta Wing
Euler and Navier-Stokes results are presented for a blunt delta wing at Mach 7.15 and 300 angle of attack. The viscous calculations were done at a Reynolds number based on chord of 5.85 x 106 with freestream and wall temperatures set to 74K and 288K respectively. The inviscid simulations were ca...
| Main Author: | |
|---|---|
| Format: | Technical Report |
| Published: |
Aerospace Computational Design Lab, Dept. of Aeronautics & Astronautics, Massachusetts Institute of Technology
2012
|
| Online Access: | http://hdl.handle.net/1721.1/70568 |