Mn 
Cd 
X_{cp
AeroCFD} 
X_{cp
AeroCP} 
Cd_{base} 
Shock
Angle
AeroCFD (deg) 
Shock
Angle
NACA 1135 (deg) 
0.30 
0.796 
0.741 
0.65 
0.127 
NA 
NA 
1.38 
0.653 
0.804 
0.65 
0.180 
45.5 
45.5 
2.0 
0.552 
0.704 
0.65 
0.147 
30.0 
30.0 
4.0 
0.392 
0.515 
0.65 
0.065 
15.0 
15.0 
6.0 
0.279 
0.413 
0.65 
0.065 
11.0 
11.0 
AeroCFD Rocket Analysis 
Mach 2
Figure3a, High power rocket CFD
analysis after 100 iterations at Mach 2. Mach contours
show 30 deg shock angle.
AeroCFD Base Flow
Analysis  Sting Mounted Rocket  Mach 2 
Figure3b, High power
rocket CFD analysis after 100 iterations at Mach 2. Mach
contours show 30 deg shock angle.
Sting added to illustrate how base flow is modeled in
the base region of a rocket. Line contours not plotted.

AeroCFD Rocket Analysis 
Mach 4
Figure4, High power rocket CFD
analysis after 100 iterations at Mach 4. Mach contours show
15 deg shock angle.

AeroCFD Rocket Analysis 
Mach 6
Figure5, High power rocket CFD
analysis after 100 iterations at Mach 6. Mach contours show
11 deg shock angle. 
Figure6a, Results from
commercial CFD*
program 
Figure6b
AeroCFD, 45.5 deg shock angle (M = 1.38)

Figure6c
AeroCFD, 11 deg shock
angle (M = 6) 
Figure6a shows that in the hands of inexperienced users
commercial CFD programs can provide incorrect results.
Figure6b and Figure6c, AeroCFD at M = 1.38 showing shock
angle is 45.5 degrees and at M = 6 shock angle is 11
degrees.
*This image from a commercially available CFD package (NOT
AeroCFD) incorrectly displays a maximum velocity of 407
m/sec in the spectrum plot or approximately M = 1.38 which
does NOT agree with a shock angle of 11 degrees for the M =
6 velocity contours displayed in Figure6a.
Web Site Design by John Cipolla/AeroRocket.com 
