A simple modification of classical unsteady thin airfoil theory is presented which accounts for the presence and induced motion of the embedded partial chord shock waves which appear at supercritical transonic Mach numbers. The basic model is found to be divergent at zero frequency because of an unbounded growth of the shock excursion amplitude. This behavior is eliminated by introducing a term associated with the mean flow Mach number gradient near the shock. Numerical results are given for the loads induced by an oscillating flap. (Stoehr)
Unsteady thin airfoil theory for transonic flows with embedded shocks
Anwendung der Tragfluegeltheorie fuer Stroemungen im schallnahen Bereich mit Stosswellen
AIAA Journal ; 18 , 6 ; 615-624
1980
10 Seiten, 10 Bilder, 1 Tabelle, 17 Quellen
Article (Journal)
English