Accession Number : AD0049045


Title :   Determination of the Characteristics of Tapered Wings


Descriptive Note : Technical rept.


Corporate Author : NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS LANGLEY FIELD VA LANGLEY AERONAUTICAL LABORATORY


Personal Author(s) : Anderson, Raymond F


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/049045.pdf


Report Date : 01 May 1936


Pagination or Media Count : 24


Abstract : Tables and charts for use in determining the characteristics of tapered wings are presented. Theoretical factors are given from which the following characteristics of tapered wings may be found: The span lift distribution, the induced-angle-of-attack distribution, the lift-curve slope, the angle of zero lift, the induced drag, the aerodynamic- center position, and the pitching moment about the aerodynamic center. The wings considered cover the complete range of taper ratios and a range of aspect ratios from 2 to 20. The factors given include the effects of sweepback and twist and apply to wings having a straight taper planform with rounded tips and an elliptical plan form. The general formulas of the usual wing theory are also given from which the characteristics of a wing of any form may be calculated when the section characteristics are known from experiment. In addition to the tables and charts, test results are given for nine tapered wings, including wings with sweepback and twist. The test results verify the values computed by the methods presented in the first part of the report. A final section is given outlining a method for estimating the lift coefficient at which a tapered wing begins to stall. This method, which should be useful for estimating the maximum lift coefficient of tapered wings, is applied to one of the wings tested.


Descriptors :   *AERODYNAMIC CHARACTERISTICS , *WINGS , AERODYNAMIC DRAG , AERODYNAMIC LIFT , AERODYNAMICS , AIRFOILS , ANGLES , COEFFICIENTS , DETERMINATION , MOMENTS , PITCH(MOTION) , STALLING , TAPER , TEST AND EVALUATION , THEORY


Subject Categories : Aircraft
      Aerodynamics


Distribution Statement : APPROVED FOR PUBLIC RELEASE