Typical AeroCFD
High Power Rocket Analysis

Copyright 1999-2015 John Cipolla/AeroRocket

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Figure-1, High power rocket rocket geometry (inches) defined for analysis.
 


Define Fluid properties, Mach number and AOA.
 

Define Airframe using library or imported shapes.
 

Define fin cross-section and fin shape.
 

Mesh flow and cluster grids around airframe.
 

Define Solution Type, CFL, NIT and SOLVE.

Plot M, P, R or T contours, etc.

Figure-2. Perform high power rocket CFD in six simple steps. This analysis required less than 15 minutes per Mach number .

Table-1, AeroCFD Results (ALT = 150k ft)

Mn Cd Xcp
AeroCFD
Xcp
AeroCP
Cdbase 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

Figure-3a, 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

 Figure-3b, 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

Figure-4, High power rocket CFD analysis after 100 iterations at Mach 4. Mach contours show 15 deg shock angle.
 

AeroCFD Rocket Analysis - Mach 6

Figure-5, High power rocket CFD analysis after 100 iterations at Mach 6. Mach contours show 11 deg shock angle.

 


Figure-6a, Results from commercial CFD* program

Figure-6b
AeroCFD, 45.5 deg shock angle (M = 1.38)

 

Figure-6c
AeroCFD, 11 deg shock angle (M = 6)

Figure-6a shows that in the hands of inexperienced users commercial CFD programs can provide incorrect results.
Figure-6b and Figure-6c, 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 Figure-6a.


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