Although significant advances have been made in inverse airfoil design methodology, the tailoring of an airfoil to maximize one or more aircraft performance parameters still involves cycling between airfoil design and aircraft performance computations. This paper presents a design formulation that incorporates aircraft performance considerations in the inverse design of laminar-flow airfoils. Two aircraft performance parameters are considered: level-flight maximum speed and maximum range. It is shown that the lift coefficient for the lower and upper corners of the airfoil low-drag range can be appropriately adjusted to tailor the airfoil for these two aircraft performance parameters. The design problem is posed as apart of a multidimensional Newton iteration in an existing conformal-mapping based inverse design code, PROFOlL. This formulation automatically adjusts the lift coefficients for the corners of the low-drag range as required for the airfoil-aircraft matching. Three examples are presented to illustrate the process for a general aviation aircraft and the results are validated by comparison with results from post-design aircraft performance computations.
Incorporation of aircraft performance considerations in inverse airfoil design
Berücksichtigung von Flugleistungsbetrachtungen in den inversen Profilentwurf
AIAA Applied Aerodynamics Conference, 21 ; 233-242
2003
10 Seiten, 16 Bilder, 1 Tabelle, 14 Quellen
Conference paper
English
Incorporation of Aircraft Performance Considerations in Inverse Airfoil Design
Online Contents | 2005
|AIAA-2003-3499 Incorporation of Aircraft Performance Considerations in Inverse Airfoil Design
British Library Conference Proceedings | 2003
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