Supercritical cascade flow analysis with shock-boundary layer interaction and shock-free redesign Article

Niederdrenk, P, Sobieczky, H, Dulikravich, GS. (1987). Supercritical cascade flow analysis with shock-boundary layer interaction and shock-free redesign . 109(3), 413-419. 10.1115/1.3262121

cited authors

  • Niederdrenk, P; Sobieczky, H; Dulikravich, GS

authors

abstract

  • This paper describes improvements made in a user-oriented analysis code for steady two-dimensional transonic flows in turbomachinery cascades. The full potential equation is solved by a finite area technique, using a C-type grid and an analytical wake model. Solution adaptive grid clustering refines the inviscid computationally captured shock. The boundary layer is computed by an integral method except in the shock region, where the analytical interaction model of Bohning and Zierep smoothes out the pressure distribution on the airfoil surface. The code is applied in its analysis and design modes to an experimentally tested cascade of airfoils. © 1987 ASME.

publication date

  • January 1, 1987

Digital Object Identifier (DOI)

start page

  • 413

end page

  • 419

volume

  • 109

issue

  • 3