Optimum Tail Plane Design for SailplanesClassical drag equations in a modern version were used to calculate the influence of tail modifications on the drag of a standard class sailplane. The profile drag which depends on the Reynolds number is included in the calculations. Minimum drag is compared with real drag for two lift coefficients. Some results have no clear tendency but low tail area and relatively low tail aspect ratio give some advantages. Optimum and real lift ratios between wing and tail plane are compared for the original sailplane.
Document ID
19790015721
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Mayland, K. (Technische Hochschule Darmstadt, Germany)
Date Acquired
August 9, 2013
Publication Date
January 1, 1979
Publication Information
Publication: NASA. Langley Res. Center The Sci. and Technol. of Low Speed and Motorless Flight, Pt. 1