Applications of AUSM+ Scheme on Subsonic, Supersonic and ...

1.6
1.4
1.2
1.0
Cl 0.8
0.6
0.4
0.2
0.0
0 2 4 6 8 10 12 14
α (deg)
Fig. 4 Drag coefficient vs AoA for clean GLC305 airfoil
From figures 6 to 9 cone cylinder and cone cylinder with
fins contours and graphs are plotted. The cone cylinder body
configurations are simulated and mach 4 other test conditions
are given in ref.16 and the finned missile [17] is simulated at
different Mach number as shown in the graph. The results for
AUSM scheme have a satisfactory agreement with the
experimental and Roe scheme and other available data.
0.025
0.020
0.015
0.010
Cm
0.005
0.000
-0.005
-0.010
Re = 3x10 6
Numerical M=0.12
Experimental M=0.12
Numerical M=0.21
Experimental M=0.21
Numerical M=0.28
Experimental M=0.28
0 2 4 6 8 10 12 14
α (deg)
Fig. 5 Pitching moment coefficient vs AoA for clean GLC305 airfoil
at different Mach number
World Academy <strong>of</strong> Science, Engineering and Technology 49 2011
Numerical
M=0.12
M=0.21
M=0.28
245
Fig. 6 Mach number contours for cone cylinder at mach 4 angle <strong>of</strong>
attack 4 o
Fig. 7 Contours <strong>of</strong> Mach number and pressure for AUSM scheme at
angle <strong>of</strong> attack 1 o .