Search
Now showing items 1-1 of 1
Numerical Simulation of Hypersonic Flow Over a Blunt Leading Edge Delta Wing
(Aerospace Computational Design Lab, Dept. of Aeronautics & Astronautics, Massachusetts Institute of Technology, 1989-10)
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 ...