Improvements to the kernel function method of steady, subsonic lifting surface theory
National Aeronautics and Space Administration, 1974 - 54 pages
The application of a kernel function lifting surface method to three dimensional, thin wing theory is discussed. A technique for determining the influence functions is presented. The technique is shown to require fewer quadrature points, while still calculating the influence functions accurately enough to guarantee convergence with an increasing number of spanwise quadrature points. The method also treats control points on the wing leading and trailing edges. The report introduces and employs an aspect of the kernel function method which apparently has never been used before and which significantly enhances the efficiency of the kernel function approach.
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THE BASIC METHOD OF SOLUTION
CHOICE OF CONTROL POINTS
1 other sections not shown
aerodynamic center Aerodynamic Lifting Surface AIAA artificial rounding technique aspect ratio British A.R.C. R&M calculating the influence center of pressure chord chordwise control points chordwise pressure mode CIRCULAR WING control point distribution control point duplication control surface convergence correct the pressure current method downwash modes edge control points elliptic integral exact result Figure finite Garner Improper Integrals influence functions influence matrix integral equation integrand kernel function method kink or crank kinks and cranks Labrujere Lamar leading and trailing leading edge lift coefficient Lifting Surface Theory Mangier Multhopp distribution Multhopp's formula NASA number of chordwise number of spanwise numbers expressed obtained by Jordan present method pressure expansion procedure Program for Aerodynamic radian rate of convergence results obtained shown singularities spanwise control points spanwise integration points spanwise pressure modes subset Subsonic Lifting Surface total number trailing edge Wagner distribution Warren 12 wing wing edge kinks ZIOOO'I ZIOOO'I ZIOOO'I