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Differences in the aerodynamic performance data obtained at different test facilities
were observed for the Wortmann FX-63-l37 airfoil. Earlier investigations
found that the size of the hysteresis loop was affected by the tunnel environment
and that single strut mounting of a three dimensional wing model interfered
negligibly with the wing. Theoretical and experimental evaluations of a half wing
model mounted with an end plate gap were done. Vortex panel method was used
in the theoretical evaluation. The results from this indicated an effect of reduced
aspect ratio with increase in end plate gap size.
Tests were conducted in the VPI Stability Tunnel at low Reynolds numbers for
different gap sizes including sealed gap. Results from the experiments showed
that even very small gaps produce substantial changes in zero lift angle of attack
(Î±u) and the change in Î±u, was reduced as Reynolds number increased. Sealed
gap test results did not show such a behavior. Flow visualization of the flow
through the gap showed a significant flow through the gap even at very low
Reynolds number and small gap size.