Applying simple extension of conventional concept of vortex system of linear airfoil theory, nonlinear dependence of aerodynamic coefficients on angle of attack can be given; computation carried out by means of system of equations, based on linear theory. English translation from Zeit fuer Flugwissenschaften, Sept 1957, indexed in Engineering Index 1957 p 57 under Aircraft Wings.
Nonlinear airfoil theory for rectangular wings in compressible flow
NASA -- Report
1959
14 pages
Report
English
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Unsteady compressible flow simulation around low-aspect-ratio rectangular flat wings
Online Contents | 2011
|Unsteady compressible flow simulation around low-aspect-ratio rectangular flat wings
SAGE Publications | 2011
|