NASA NTRS · 19990051022
Airfoil Design Using a Coupled Euler and Integral Boundary Layer Method with Adjoint Based Sensitivities
Abstract
The objective of this paper is to present a control theory approach for the design of airfoils in the presence of viscous compressible flows. A coupled system of the integral boundary layer and the Euler equations is solved to provide rapid flow simulations. An adjunct approach consistent with the complete coupled state equations is employed to obtain the sensitivities needed to drive a numerical optimization algorithm. Design to target pressure distribution is demonstrated on an RAE 2822 airfoil at transonic speed.
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Edwards, S., Reuther, J., Chattot, J. J.. 1997-01-01. Airfoil Design Using a Coupled Euler and Integral Boundary Layer Method with Adjoint Based Sensitivities. https://ntrs.nasa.gov/citations/19990051022
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