university of florida thesis or dissertation formatting template
university of florida thesis or dissertation formatting template
university of florida thesis or dissertation formatting template
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consisting <strong>of</strong> viscous, rigid, full-scale models <strong>of</strong> the F-16. Three <strong>of</strong> these grids are seen in Figure<br />
5-2. The left side <strong>of</strong> the figures shows the surface grid on the wing and the right side the<br />
computational grid at 88% span station. The engine duct is modeled and meshed up to the engine<br />
face f<strong>or</strong> all cases.<br />
The initial grid examined, listed in Table 5-1 as Grid0, models the f<strong>or</strong>ebody bump,<br />
diverter, and ventral fin. The wing-tip missile and c<strong>or</strong>responding attachment hardware and the<br />
nose boom are not modeled. This computational grid is identical to the grid used by Dean 116 and<br />
Görtz 117 f<strong>or</strong> their development <strong>of</strong> an efficient computational method f<strong>or</strong> accurately determining<br />
static and dynamic stability and control (S&C) characteristics <strong>of</strong> a high-perf<strong>or</strong>mance aircraft.<br />
This grid is also extensively validated by Dean f<strong>or</strong> whole aircraft f<strong>or</strong>ces and moments against the<br />
ATLAS database provided by the aircraft manufacturer. The half-span aircraft surface grid<br />
comprises 1.09 million points (3.42 million cells) and is considered the “coarse” grid examined,<br />
as it is the lowest refinement. The cells are concentrated in the strake v<strong>or</strong>tex and quarter-ch<strong>or</strong>d<br />
regions, as seen in Figure 5-2 A) and D).<br />
The medium-refinement grid is listed as Grid4 in Table 5-1. The half-span version <strong>of</strong><br />
Grid4 consists <strong>of</strong> 1.77 million points (5.6 million cells) and models the same components as<br />
Grid0, but adds the fuselage gun-p<strong>or</strong>t and leading-edge antennae in addition to the tip launcher<br />
and attachment hardware. Grid4, seen in Figure 5-2 B) and E), has unif<strong>or</strong>m refinement over the<br />
entire wing with source surfaces in tip and strake v<strong>or</strong>tex regions.<br />
Grid9 is the fine-refinement clean-wing aircraft grid in Table 5-1 consisting <strong>of</strong> 3.08 million<br />
points (9.0 million cells). Grid8 is the fine-refinement grid in Table 5-1 that models the aircraft<br />
with tip launcher and consists <strong>of</strong> 3.18 million points (9.27 million cells). Both Grid8 and Grid9<br />
model the f<strong>or</strong>ebody bump, diverter, ventral fin, fuselage gun-p<strong>or</strong>t, and leading-edge antennae.<br />
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