*
This program determines the complete viscous
and inviscid flow around a body of revolution at a given angle of attack
and traveling at supersonic speeds. The viscous calculations from this
program agree with experimental values for surface and pitot pressures
and with surface heating rates. At high speeds, lee-side flows are
important because the local heating is difficult to correlate and
because the shed vortices can interact with vehicle components such as
a canopy or a vertical tail. This program should find application in
the design analysis of any high speed vehicle.
*

*
Lee-side flows are difficult to calculate because thin-boundary-layer
theory is not applicable and the concept of matching inviscid and
viscous flow is questionable. This program uses the parabolic
approximation to the compressible Navier-Stokes equations and solves
for the complete inviscid and viscous regions of flow, including the
pressure. The parabolic approximation results from the assumption that
the stress derivatives in the streamwise direction are small in
comparison with derivatives in the normal and circumferential
directions. This assumption permits the equation to be solved by an
implicit finite difference marching technique which proceeds downstream
from the initial data point, provided the inviscid portion of flow is
supersonic. The viscous cross-flow separation is also determined as part
of the solution. To use this method it is necessary to first determine
an initial data point in a region where the inviscid portion of the
flow is supersonic.
*

This program was released through COSMIC as program ARC-11087. The italicized text above is from the official COSMIC release.

- Go to the page of references for the AOFA program.
- Download aofa.zip, containing the original source code, the source code converted to modern Fortran, and the input for a test case.