The Kasprzyk slotted flap glider airfoil (the Kasper wing) enabling glider flight at 32 km/h and 0.5 m/sec descent speed was wind tunnel tested in the U.S. The test layout is described and reasons offered for discrepancies between wind tunnel results and Polish in flight data: high induced drag caused by relative size of model wing span and tunnel, by vortex attenuators on the model and their proximity to the tunnel wall, nonsimilarity between flow over a smooth wing and flow over the Kasprzyk wing with bound vortices, obstruction of the tunnel test chamber cross section by the model wing, discrepant Reynolds numbers, and model airfoil aspect ratio much smaller than the prototype. The overall results offer partial confirmation of the Kasprzyk theory, but further in tunnel and in flight studies are recommended.
Kasprzyk airfoil. The first wind-tunnel tests
1984-10-01
Miscellaneous
No indication
English
Kasprzyk Airfoil. The First Wind-Tunnel Tests
NTIS | 1984
|Wind tunnel tests of the VG2-16 airfoil
British Library Conference Proceedings | 1993
|Uncertainty analysis of airfoil wind tunnel tests with automatic differentiation
Online Contents | 2014
|