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Results are chosen from both sets of wind tunnel data at Mach=0.9, and AOA=1.5° for
Elbers’ and AOA=1.0° for Sellers’. CFD results are run at Mach=0.9, AOA=1.34° (trimmed
flight condition), at 5,000 feet for a full scale F-16C with tip LAU-129 launchers. It can be seen
in the instantaneous Cp measurements plotted against non-dimensional chord at various span
locations in Figure 5-8, Figure 5-9, Figure 5-10, Figure 5-11, Figure 5-12, and Figure 5-13, that
despite the differences in configuration, the results match closely, particularly in the shock
region. Therefore based on these initial indirect comparison results, confidence can be had in the
accuracy of CFD models and code used for the research at hand. In the future, direct
comparisons can easily be made once the appropriate store models are generated.
Table 5-1. Computational grids examined.
Wing Refinement #points #cells
Grid# Components Level Half-span Full-span Half-span Full-span
Grid0 Clean coarse 1.09E+06 2.07E+06 3.42E+06 6.85E+06
Grid4 Tip Launcher/
LE Antennae
medium 1.77E+06 3.97E+06 5.60E+06 14.2E+06
Grid8 Tip Launcher/
LE Antennae
fine 3.18E+06 - 9.27E+06 -
Grid9 LE Antennae fine 3.08E+06 - 9.00E+06 -
Wing1 Tip Launcher/
LE Antennae
fine 2.25E+06 - 5.87E+06 -
56