Turbulence
Models and Their Application
With Computer Programs |
Test Case for NACA 0012 Airfoil:
a) RL=0; Mach = 0.10
input data: m1rm0.inp
output data: Panel Method m1rm0Panel.out
Summary m1rm0Summary.out and m1rm0Summary.bdf
b) RL=3000000.0; Mach = 0.10
input data: m1rm3.inp
output data: Panel Method m1rm3Panel.out
IBL Method m1rm3ibl.out
Summary m1rm3Summary.out and m1rm3Summary.bdfc) RL=4000000.0; Mach = 0.10
input data: m1rm4.inp
output data: Panel Method m1rm4Panel.out
IBL Method m1rm4ibl.out
Summary m1rm4Summary.out and m1rm4Summary.bdfd) RL=5000000.0; Mach = 0.10
input data: m1rm5.inp
output data: Panel Method m1rm5Panel.out
IBL Method m1rm5ibl.out
Summary m1rm5Summary.out and m1rm5Summary.bdfThe summary m1Summary.xls and m1Summary.pdf.
Copyright (c) Horizons Publishing Inc. 2004