Numerical optimization design of advanced transonic wing configurations
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Numerical optimization design of advanced transonic wing configurations

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Published by National Aeronautics and Space Administration, Ames Research Center in Moffett Field, Calif .
Written in English

Subjects:

  • Transonic planes -- Wings

Book details:

Edition Notes

StatementGary B. Consentino, Terry L. Holst
SeriesNASA technical memorandum -- 85950
ContributionsHolst, Terry L, Ames Research Center
The Physical Object
FormatMicroform
Pagination1 v.
ID Numbers
Open LibraryOL14926478M

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shape optimization problems such as airfoil shape design [7,8], Multi-element airfoil shape design [9], subsonic wing shape design [10] and supersonic wing shape design [11]. The previous applications of numerical optimization methods, however, are restricted to more or less simplified problems involving not more than design Size: KB. Wing design by numerical optimization. Application of Computational Methods to Transonic Wing Design. 23 August A F?LL POTENTIAL INVERSE METHOD BASED ON A DENSITY LINEARIZATION SCHEME FOR WING DESIGN. Numerical optimization design of advanced transonic wing configurations. The use of numerical optimization for transonic aerodynamic shape design was pioneered by Hicks, Murman and Vanderplaats [13]. They applied the method to two-dimensional profile design subject to the potential flow equation. The method was quickly extended to wing design File Size: 1MB. A numerical optimization method of wing design. by solving adjoint equations based on Euler. equations is studied for better considering. performance requirements of wing design in this. paper.

  Challenges, Ideas, and Innovations of Joined-Wing Configurations: A Concept from the Past, an Opportunity for the Future Progress in Aerospace Sciences, Vol. 87 Transonic Aerodynamics Analysis for Multidisciplinary Design Optimization ApplicationsCited by: The flying wing or blended wing body seems to be one of the most promising configurations to reach a higher efficiency than current configurations, justifying the efforts recently devoted to. The procedure for wing aerodynamic design based on the algorithm of simultaneous multiregime optimization of cruise and low-speed performance is considered. The method is based on the combination of fast direct methods for subsonic and transonic wing analysis, geometry variation module and the optimization procedure. The description of all the. The use of numerical optimization for transonic aerodynamic shape design was pioneered by Hicks, Murman and Vanderplaats [13]. They applied the method to tw*dimensional profile design subject to the potential flow equation. The method was quickly extended to wing design .

To design the inner wing, an optimization of the inner airfoil geometry and the wing twist with the lift-to-drag ratio as objective function has been conducted in the first step. Summary. Wing design based upon inverse methods has become the standard procedure in the past. However, the design is limited to one single design point and the quality of the result depends upon the experience of the designer. Direct optimization allows to avoid these disadvantages. Because of the long calculation times of three-dimensional flow Author: O. Frommann, D. Forbrich. The paper presents an optimization technique applied to the transonic-wing design of the MOB BWB aircraft studied by Ciampa et al.3 A good deal of the aerodynamic design work has been carried out with Euler-based optimization tech-niques and the results have demonstrated the potential for ‘discovering’ aerodynamically e cient features of. NUMERICAL OPTIMISATION OF ADAPTIVE TRANSONIC AIRFOILS WITH VARIABLE CAMBER Fig. 3 Isobars in the shock region of a DA VA2 airfoil at M∞ 0: 77 and c l 0 (result MU- FLO). Fig. 4 Isobars in the shock region of a DA VA2 airfoil with an optimised SCB applied at.