A compressible, unsteady, full Navier-Stokes, finite difference code has been developed for modeling transonic flow through two-dimensional, oscillating cascades. The procedure introduces a deforming grid technique to capture the motion of the airfoils. Results using a deforming grid are presented for both isolated and cascaded airfoils. The load histories and unsteady pressure distributions are predicted for the NACA 64A010 isolated airfoil and compared with existing experimental data. Results show that the deforming grid technique can be used to successfully predict the unsteady flow properties around an oscillating airfoil. The deforming grid technique has been extended for modeling unsteady flow in a cascade. The use of a deforming grid simplifies the specification of boundary conditions. Unsteady flow solutions similar to the isolated airfoil predictions are found for a NACA 0012 cascade with zero interblade phase angle and zero stagger. Experimental data for these cases are not available for code validation, but computational results are presented to show sample predictions from the code. Applications of the code to typical turbomachinery flow conditions will be presented in future work.
Numerical simulations of unsteady, viscous, transonic flow over isolated and cascaded airfoils using a deforming grid
Numerische Simulierung der instationaeren viskosen Ueberschallstroemung an isolierten und kaskadenfoermig angeordneten Tragflaechen mit einem Leitgitter
AIAA-Papers ; Jun ; 1-14
1987
14 Seiten, 15 Bilder, 1 Tabelle, 13 Quellen
Conference paper
English
Calculations of viscous transonic flow over airfoils
AIAA | 1984
|Unsteady Viscous Flow Simulations by a Fully Implicit Method with Deforming Grid
British Library Conference Proceedings | 2005
|