TY - GEN
T1 - A multipoint inverse method for multi-element airfoil design
AU - Gopalarathnam, Ashok
AU - Selig, Michael S.
N1 - Publisher Copyright:
© 1996 by Ashok Gopalarathnam and Michael S. Selig. Published by the American Institute of Aeronautics and Astronautics, Inc.
PY - 1996
Y1 - 1996
N2 - A multipoint inverse method for the design of multi-element airfoils is presented. The method uses an isolated-airfoil, multipoint, inverse code to generate each element of the multi-element airfoil and a two dimensional panel method is used to analyze the multi-element airfoil. The isolated airfoil inviscid velocity distributions are used as design variables to achieve prescribed inviscid velocity distributions for the multi-element airfoil. Each element is divided into segments. The isolated airfoil velocity distribution over each segment at a specified lift coefficient is adjusted to achieve the desired velocity distribution over the corresponding segment of the multielement airfoil at the specified operating condition. This procedure is automated using an efficient multidimensional Newton iteration. The method thus allows for rapid, interactive design of a multi-element airfoil with a desired inviscid behavior, which can then be analyzed using more computationally demanding viscous codes.
AB - A multipoint inverse method for the design of multi-element airfoils is presented. The method uses an isolated-airfoil, multipoint, inverse code to generate each element of the multi-element airfoil and a two dimensional panel method is used to analyze the multi-element airfoil. The isolated airfoil inviscid velocity distributions are used as design variables to achieve prescribed inviscid velocity distributions for the multi-element airfoil. Each element is divided into segments. The isolated airfoil velocity distribution over each segment at a specified lift coefficient is adjusted to achieve the desired velocity distribution over the corresponding segment of the multielement airfoil at the specified operating condition. This procedure is automated using an efficient multidimensional Newton iteration. The method thus allows for rapid, interactive design of a multi-element airfoil with a desired inviscid behavior, which can then be analyzed using more computationally demanding viscous codes.
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U2 - 10.2514/6.1996-2396
DO - 10.2514/6.1996-2396
M3 - Conference contribution
AN - SCOPUS:84964204671
SN - 9781563472121
T3 - 14th Applied Aerodynamics Conference
SP - 197
EP - 205
BT - 14th Applied Aerodynamics Conference
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - 14th Applied Aerodynamics Conference, 1996
Y2 - 17 June 1996 through 20 June 1996
ER -