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CONE-CYLINDER:
MACH NUMBER = 6.86, AOA = 6.7 DEGREES
The following plots compare supersonic wind tunnel data
and AeroCFD results using the Plot Options capability.
In this example, Mach number = 6.86 and AOA = 6.7 degrees for
flow past a cone-cylinder body. PLOT-1 displays P/Pinf at station
X/L = 0.231 and PLOT-2 displays P/Pinf on the windward meridian
(180 degrees). Supersonic wind tunnel data is represented by
the o symbols and
AeroCFD
analysis results are represented by the
red lines. Solution converged in 100 iterations and
took 12 minutes and 10 seconds on a Pentium 4 home computer.
Reference: AIAA-89-0524, "Hypersonic Prediction Comparisons
with Experimental Data for a Cone-Cylinder at Mach 6.86".
NOTE: Experimental X-DATA and Y-DATA are input in the PLOT
OPTIONS section and saved using the Save (disk) icon. Data is
read using the Open (folder) button and plotted using the Plot
icon (4th icon from left) for PLOT 1 and PLOT 2 data points. The
other buttons Delete, Clear and Scale plot results. All point by
point experimental data are plotted with the AeroCFD results
that were selected from the Surface Parameter Distribution
section, Cp, P/P0, T/T0, M, R/R0.
Cone-Cylinder,
Mach number = 6.86, AOA = 6.7 degrees. Wind Tunnel Data Verses
AeroCFD. Windward Meridian.
(2) The following
compares supersonic wind tunnel data and AeroCFD results using
the Plot Options capability. In this example, Mach number
= 6.86 and AOA = 6.7 degrees for flow past a cone-cylinder body.
PLOT-1 displays P/Pinf at station X/L = 0.758 and PLOT-2 displays
P/Pinf on the 90 degree meridian (90 degrees).
Cone-Cylinder,
Mach number = 6.86, AOA = 6.7 degrees. Wind Tunnel Data Verses
AeroCFD. 90 Degree Meridian
(3) The following compares supersonic wind tunnel data and
AeroCFD
results using the Plot Options capability. In this example,
Mach number = 6.86 and AOA = 6.7 degrees for flow past a cone-cylinder
body. PLOT-1 displays P/Pinf at station X/L = 0.758 and PLOT-2
displays P/Pinf on the leeward meridian (0.0 degrees). Additionally,
the measured wind tunnel center of pressure location (XCP/L)
is .445 and AeroCFD predicts the center of pressure location
(XCP/L) to be .454.
Cone-Cylinder,
Mach number = 6.86, AOA = 6.7 degrees. Wind Tunnel Data Verses
AeroCFD. Leeward Meridian. |
