AeroCFD: Data Plot Options
Instructions, Main Page

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.


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