See notes below for program information and limitations.

Aero 301

Aero 302

Aero 309

Aero 420

ES 312

AeroTools

1) Inviscid flow analysis is constant source/vortex sheet method utilizing 50 upper and 50 lower surface panels.

2) Mach correction is via Prandlt-Glauert and is invalid if surface pressure coefficients exceed the critical pressure coefficient (Cp cr), i.e. if the local flow exceeds Mach = 1.0.

3) Viscous analysis is done by integral methods:  Pohlhausen for laminar flow and Ferziger et al., for turbulent flow.  Natural transition is predicted using Granville's method.  Transition is forced at laminar separation locations.  Viscous analysis does NOT handle separated flow.