Viscous computation of a space shuttle flow field
Abstract
A procedure is presented, as well as some results, to calculate the flow over the winged orbiter. This necessitates the use of two computer codes. A parabolized marching Navier-Stokes code is used to obtain the solution up to the bow shock-wing shock interaction region and for the region after the interaction. An unsteady Navier-Stokes code is to be used in the region of the shock interaction. Only resuls for the marching code are presented. For the flow conditions calculated, M infinity = 7.9, alpha = 25 deg, T(wall) = 540 R, Re(L) = 60728 per inch, laminar or turbulent, the PNS code was marched up to an X/L = 0.7 which is where the bow shock-wing shock interaction region occurs.
- Publication:
-
NASA STI/Recon Technical Report N
- Pub Date:
- June 1984
- Bibcode:
- 1984STIN...8430225C
- Keywords:
-
- Computational Fluid Dynamics;
- Space Shuttle Orbiters;
- Supersonic Flow;
- Viscous Flow;
- Bow Waves;
- Laminar Flow;
- Navier-Stokes Equation;
- Pressure Distribution;
- Shock Wave Interaction;
- Turbulent Flow;
- Unsteady Flow;
- Wings;
- Fluid Mechanics and Heat Transfer