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An accurate drag polar is the starting point for all sailplane performance calculations.
However, most of the existing literature in this area (for example Fiecke [79] and Hoemer[10]) is directed towards the calculation of the performance of powered aircraft and thus lacks data for Reynolds numbers typical of modern sailplanes.
Figure 191 presents representative drag polars calculated for several sailplanes.
Sailplane airfoils typically operate at Reynolds numbers at which the boundary-layer transition characteristics are highly sensitive lo factors such as airfoil geometry, surface quality, and free stream turbulence.
To date, the majority of wind-tunnel investigations for sailplane airfoils have been made by F.
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