Integrating CFD and Experiment in Aerodynamics - CFD4Aircraft
Integrating CFD and Experiment in Aerodynamics - CFD4Aircraft Integrating CFD and Experiment in Aerodynamics - CFD4Aircraft
19 Figure 5: Time history of average and difference of breakdown locations showing asymmetric oscillations. Figure 6: Asymmetric structural mode for a slightly flexible delta wing when vortex breakdown occurred on the wing.
20 Figure 7: Flow visualisation of vortices over a nonslender delta wing with a sweep angle of Λ = 50 o (left). Dual vortex structure (of the sane sign of vorticity) in a cross-flow plane exists upstream of vortex breakdown (right), alpha = 15 o . Figure 8: Surface flow visualisation for Λ = 50 o for α = 2.5 o (left) and α = 15 o (right).
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20<br />
Figure 7: Flow visualisation of vortices over a nonslender delta w<strong>in</strong>g with a sweep angle of Λ = 50 o<br />
(left). Dual vortex structure (of the sane sign of vorticity) <strong>in</strong> a cross-flow plane exists upstream of<br />
vortex breakdown (right), alpha = 15 o .<br />
Figure 8: Surface flow visualisation for Λ = 50 o for α = 2.5 o (left) <strong>and</strong> α = 15 o (right).
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