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 NavierStokes code is used to obtain the solution over a wingcanopy 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;
 NavierStokes Equation;
 Reynolds Number;
 Fluid Mechanics and Heat Transfer