Abstract
THE yawing effects of the unsymmetrical vortex system caused by deflected ailerons are known to be modified by the presence of wind-tunnel walls. This modification has been calculated by Koning and van der Maas for the case of a single aileron extending to the tip of the wing. The present calculation differs from that of Koning and van der Maas in the following respects: (1) The ailerons may be set in from the tips. (2) The modification for the case where two ailerons are deflected is determined. (3) Suitable non-dimensional parameters are found by means of which the results can be presented in an easily useable form. The following symbols are used :
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