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An approach to the constrained design of natural laminar flow airfoilsA design method has been developed by which an airfoil with a substantial amount of natural laminar flow can be designed, while maintaining other aerodynamic and geometric constraints. After obtaining the initial airfoil's pressure distribution at the design lift coefficient using an Euler solver coupled with an integml turbulent boundary layer method, the calculations from a laminar boundary layer solver are used by a stability analysis code to obtain estimates of the transition location (using N-Factors) for the starting airfoil. A new design method then calculates a target pressure distribution that will increase the larninar flow toward the desired amounl An airfoil design method is then iteratively used to design an airfoil that possesses that target pressure distribution. The new airfoil's boundary layer stability characteristics are determined, and this iterative process continues until an airfoil is designed that meets the laminar flow requirement and as many of the other constraints as possible.
Document ID
19960042762
Document Type
Thesis/Dissertation
Authors
Green, Bradford Earl (George Washington Univ. Washington, DC United States)
Date Acquired
September 6, 2013
Publication Date
July 1, 1995
Subject Category
Aerodynamics
Report/Patent Number
NASA-TM-111860
NAS 1.15:111860
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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