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A multi-point inverse airfoil design method based on conformal mappingAn exact method of multipoint inverse airfoil design for incompressible flow is presented. Multipoint design is handled by dividing the airfoil into a number of desired segments. For each segment the velocity distribution is prescribed together with an angle of attack at which the prescribed velocity distribution is to be achieved. In this manner, multipoint design objectives can be taken into account in the initial specification of the velocity distribution. In order for the multipoint inverse airfoil design problem to be well posed, three integral constraints and several conditions arise which must be satisfied. Further restrictions are imposed if the airfoil is to have a specified pitching moment, thickness ratio, or other constraints. The system of equations is solved partly as a linear system and partly through multidimensional Newton iteration. Since the velocity distribution is prescribed about the circle in the angular coordinate, specification of the velocity in terms of arc length is handled through the multidimensional Newton iteration as well. The current formulation sets the stage for a more general multipoint inverse airfoil design method in which it will be possible to specify the velocity distribution, some boundary-layer development, or the surface geometry along a segment.
Document ID
19910034501
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Selig, Michael S.
(Pennsylvania State Univ. University Park, PA, United States)
Maughmer, Mark D.
(Pennsylvania State University University Park, United States)
Date Acquired
August 15, 2013
Publication Date
January 1, 1991
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 91-0069
Accession Number
91A19124
Funding Number(s)
CONTRACT_GRANT: NGT-50341
Distribution Limits
Public
Copyright
Other

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