Numerical simulation of viscous supersonic flow over a generic fighter configuration
Abstract
A procedure is presented, as well as some results, to calculate the flow over a generic fighter configuration. A parabolized marching Navier-Stokes code is used to obtain the solution over a wing-canopy body. The flow conditions simulate supersonic cruise with a freestream Mach number of 2.169 and angles of attack of 4 and 10 deg. The body surface is considered to be an adiabatic wall and the flow is assumed to be turbulent for the given Reynolds number.
- Publication:
-
NASA STI/Recon Technical Report N
- Pub Date:
- December 1985
- Bibcode:
- 1985STIN...8615627C
- Keywords:
-
- Angle Of Attack;
- Canopies;
- Fighter Aircraft;
- Free Flow;
- Mathematical Models;
- Simulation;
- Supersonic Flow;
- Three Dimensional Flow;
- Turbulent Flow;
- Viscous Flow;
- Mach Number;
- Navier-Stokes Equation;
- Reynolds Number;
- Fluid Mechanics and Heat Transfer