Leading-edge singularities in thin-airfoil theoryIf the thin airfoil theory is applied to an airfoil having a rounded leading edge, a certain error will arise in the determination of the pressure distribution around the nose. It is shown that the evaluation of the drag of such a blunt nosed airfoil by the thin airfoil theory requires the addition of a leading edge force, analogous to the leading edge thrust of the lifting airfoil. The method of calculation is illustrated by application to: (1) The Joukowski airfoil in subsonic flow; and (2) the thin elliptic cone in supersonic flow. A general formula for the edge force is provided which is applicable to a variety of wing forms.
Document ID
19760012004
Acquisition Source
Legacy CDMS
Document Type
Other
Authors
Jones, R. T. (NASA Ames Research Center Moffett Field, CA, United States)