Computation of the poststall behavior of a circulation controlled airfoil

Autor:	Samuel W. Linton
Rok vydání:	1994
Předmět:	Airfoil Physics Lift coefficient Post stall Aerospace Engineering Stall (fluid mechanics) Mechanics Physics::Fluid Dynamics Adverse pressure gradient symbols.namesake Flow separation Classical mechanics Mach number symbols Trailing edge
Zdroj:	Journal of Aircraft. 31:1273-1280
ISSN:	1533-3868 0021-8669
DOI:	10.2514/3.46647
Popis:	The physics of the circulation controlled airfoil is complex and poorly understood, particularly with regards to jet stall, which is the eventual breakdown of lift augmentation by the jet at some sufficiently high blowing rate. The present paper describes the numerical simulation of stalled and unstalled flows over a two-dimensional circulation controlled airfoil using a fully implicit Navier-Stokes code, and the comparison with experimental results. Mach numbers of 0.3 and 0.5 and jet total to freestream pressure ratios of 1.4 and 1.8 are investigated. The Baldwin-Lomax and k-epsilon turbulence models are used, each modified to include the effect of strong streamline curvature. The numerical solutions of the post-stall circulation controlled airfoil show a highly regular unsteady periodic flowfield. This is the result of an alternation between adverse pressure gradient and shock induced separation of the boundary layer on the airfoil trailing edge.
Databáze:	OpenAIRE
Externí odkaz:	https://explore.openaire.eu/search/publication?articleId=doi_________::890dd6bf9b67aee662a3425713aa0979 https://doi.org/10.2514/3.46647 Zobrazit plný text záznamu