22nd Congress of International Council of the Aeronautical Sciences, Harrogate, UK, 28 August - 1st September, 2000
Paper ICAS 2000-5.1.3
INVERSE DESIGN OF TURBOMACHINERY AIRFOILS USING THE NAVIER STOKES EQUATIONS
B. Kaplan, S. Eyi
Aeronautical Engineering, Middle East Technical University, Ankara, 06531 Turkey
Keywords: turbomachinery, airfoils, navier stokes equations, transonic, surface pressure distribution
In this paper an inverse design method is
presented which couples a Navier-Stokes flow
solver and a numerical optimization algorithm.
The design method generates a turbomachinery
airfoil, producing a specified surface pressure
distribution at a transonic speed. A least-square
optimization technique is used to minimize
pressure discrepancies between the target and
designed airfoils. In order to represent the nonlinear,
rotational and viscous physics of
transonic flows, Navier-Stokes equations are
used to predict the flow field. Sensitivity
derivatives are obtained using finite
differencing. Effects of different design
variables on the performance of design
optimization are evaluated.
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