A quadrature method is derived for calculating the incompressible-flow aerodynamics of arbitrarily cambered jet-flapped airfoils. The anticipated application of the methodology is to high-speed subsonic flows (combat maneuvering aircraft) via the use of compressible-flow similarity transformations. The method yields the aerodynamic properties in terms of integrals having integrands which consist of the product of the camber-line ordinate and an influence function which is a parametric function of the jet-momentum coefficient. In general, the integrals involved must be evaluated by numerical methods. Tables of the necessary influence functions are given in the report.
Cambered Jet-Flapped Airfoil Theory with Tables and Computer Programs for Application
1977
162 pages
Report
No indication
English
Tema Archive | 1973
|Thin-airfoil theory of an ejector-flapped wing section
AIAA | 1974
|Thin-Airfoil Theory of an Ejector-Flapped Wing Section
AIAA | 1975
|Subsonic similarity rule for jet-flapped airfoil
AIAA | 1971
|Unsteady Lift of a Flapped Airfoil by Indicial Concepts
Online Contents | 1994
|