Modification of the unsteady-flow field predicted by transonic small-disturbance equations using a Navier-Stokes solution of the steady-flow field

Thesis/Dissertation · Thu Jan 01 04:00:00 EST 1987

OSTI ID:6330885

Kinsey, D W

This first part of this report describes a numerical solution of the Navier-Stokes equations for flow over a thick supercritical airfoil with strong shock-induced separation on both the upper and lower surfaces. The separated-flow region extends from the shock (approximately 50% chord) to the trailing edge on both surfaces. The solution algorithm employed was an explicit predictor-corrector method. An algebraic turbulence model was used to describe the turbulent Reynolds stresses. There have been many approaches used to extend the useful range of two-dimensional, unsteady transonic small disturbance (TDS) procedures. The second part of this report describes another such procedure. Modifications to the TSD procedure, LTRAN2, that allow the procedure to determine the geometry corresponding to the prescribed pressure distribution from experimental data or as predicted by a Navier-Stokes solver are described. This new geometry accounts for compressible and viscous effects and is a much improved starting point for unsteady calculations.

• Research Organization: Dayton Univ., OH (USA)
• OSTI ID: 6330885
• Country of Publication: United States
• Language: English

Related Subjects

42 ENGINEERING
420400* -- Engineering-- Heat Transfer & Fluid Flow
AIRFOILS
ALGORITHMS
COMPRESSIBLE FLOW
DIFFERENTIAL EQUATIONS
EQUATIONS
FLUID FLOW
MATHEMATICAL LOGIC
NAVIER-STOKES EQUATIONS
PARTIAL DIFFERENTIAL EQUATIONS
STEADY FLOW
UNSTEADY FLOW
VISCOUS FLOW