An inviscid-viscous interaction approach to the calculation of dynamic stall initiation on airfoils

Journal Article · Fri Oct 01 00:00:00 EDT 1993 · Journal of Turbomachinery; (United States)

DOI:https://doi.org/10.1115/1.2929307· OSTI ID:5857764

Cebeci, T ^[1]; Platzer, M F ^[2]; Jang, H M; Chen, H H ^[1]

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1. California State Univ., Long Beach, CA (United States). Aerospace Engineering Dept.
2. Naval Postgraduate School, Monterey, CA (United States). Dept. of Aeronautics and Astronautics

An interactive boundary-layer method is described for computing unsteady incompressible flow over airfoils, including the initiation of dynamic stall. The inviscid unsteady panel method developed by Platzer and Teng is extended to include viscous effects. The solutions of the boundary-layer equations are obtained with an inverse finite-difference method employing an interaction law based on the Hilbert integral, and the algebraic eddy-viscosity formulation of Cebeci and Smith. The method is applied to airfoils subject to periodic and ramp-type motions and its abilities are examined for a range of angles of attack, reduced frequency, and pitch rate.

• OSTI ID: 5857764
• Journal Information: Journal of Turbomachinery; (United States), Vol. 115:4; ISSN 0889-504X
• Country of Publication: United States
• Language: English

Related Subjects

20 FOSSIL-FUELED POWER PLANTS
AIRFOILS
INCOMPRESSIBLE FLOW
COMPRESSOR BLADES
COMPRESSORS
FINITE DIFFERENCE METHOD
STEADY FLOW
TURBOMACHINERY
CALCULATION METHODS
EQUIPMENT
FLUID FLOW
ITERATIVE METHODS
MACHINERY
NUMERICAL SOLUTION
200104* - Fossil-Fueled Power Plants- Components