Analysis of transonic flow through a cascade of airfoils is investigated using the finite element method. Development of a computational grid suitable for complex flow structures and different types of boundary conditions is presented. An efficient pseudo-time integration scheme is developed for the solution of equations. Modeling of the shock and the convergence characteristics of the developed scheme are discussed. Numerical results include a 45 deg staggered cascade of NACA 0012 airfoils with inlet flow Mach number of 0.8 and angles of attack 1, 0, and 1 deg.(Wassmann)
Transonic flow computations in cascades using finite element method
Transsonische Stroemungsberechnungen in Kaskaden mit Hilfe der Finite Elemente Methode
ASME-Papers ; 1-8
1981
8 Seiten, 5 Bilder, 9 Quellen
Conference paper
English
Transonic flow computations using nonlinear potential methods
Online Contents | 2000
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