Results 131 to 140 of about 1,855 (186)

A multipoint inverse airfoil design method for slot-suction airfoils

13th Applied Aerodynamics Conference, 1995
Owing to a renewed interest in advanced-concept transport aircraft with active boundary-layer control (suction and/or blowing), a generalized multipoint method for the inverse design of airfoils with slot suction in incompressible potential flow is presented. The results predicted by theory show good agreement with experiment.
Farooq Saeed, Michael S. Selig
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Airfoil Design in Subcritical and Supercritical Flows

Journal of Applied Mechanics, 1979
The “inverse” or “design” problem in aerodynamics, which solves for the airfoil shape that induces a prescribed chordwise surface pressure subject to additional requirements on trailing edge closure, is considered in the transonic small-disturbance limit. A new formulation for the stream function ψ is suggested which uses well-set Neumann conditions on
Chin, W. C., Rizzetta, D. P.
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A new mutation operator for evolutionary airfoil design

Soft Computing, 1999
A new mutation operator, ℳ ijn , capable of operating on a set of adjacent bits in one single step, is introduced. Its features are examined and compared against those of the classical bit–flip mutation. A simple Evolutionary Algorithm, ℳ–EA, based only on selection and ℳ ijn , is ...
I De Falco, A Della Cioppa, A Iazzetta, E Tarantino   +3 more
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Breeder genetic algorithms for airfoil design optimisation

Proceedings of IEEE International Conference on Evolutionary Computation, 2002
In this paper a version of genetic algorithms, the breeder genetic algorithms, suitable for continuous parameter optimisation, has been applied and compared to a classical discrete genetic algorithm. The application concerns a typical optimisation problem in aerodynamics, the problem of determining the coordinates of an airfoil given a surface pressure
De Falco I, Del Balio R, Della Cioppa A, Tarantino E   +3 more
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New airfoil design concept

Journal of Aircraft, 1991
The present airfoil design concept is based on utilizing unconventional geometry characteristics near the airfoil trailing edge which include a finite trailing edge thickness, strongly divergent trailing edge upper and lower surfaces, and high surface curvature on the lower surface at or near the lower surface trailing edge.
Preston A. Henne, Robert D. Gregg
openaire   +1 more source

Shopfoil: Design of Unoptimized Airfoils

Volume 3: Design, Materials and Manufacturing, Parts A, B, and C, 2012
The desire and demand to fly farther and faster has progressively integrated the concept of optimization with airfoil design resulting in increasingly complex numerical tools pursuing efficiency often at diminishing returns, while the costs and difficulty associated with fabrication increases with design complexity.
Zachary G. Napolillo, Shanti D. Hamburg, Patrick H. Browning, Wade W. Huebsch, Jay Wilhelm, Mridul Gautam   +5 more
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Turbine Airfoil Design Optimization

Volume 1: Turbomachinery, 1996
A new blade design methodology, which allows designers to react rapidly to changes in functional requirements of turbines and transition quickly from concept to design, has been discussed in this paper. This methodology reduces the design cycle time by creating a three-dimensional model of the blade, through concurrent design of multiple two ...
Sanjay Goel, John I. Cofer, Hardev Singh
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Transonic Airfoil Design Code

1977
Wind tunnel tests have shown that it is feasible to design high performance supercritical wing sections by solving mathematically the inverse problem of shaping an airfoil so that the transonic flow over it becomes shockless at specified conditions. The construction of shockless flows is most effectively carried out by means of the hodo-graph method ...
Frances Bauer, Paul Garabedian, David Korn   +2 more
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Inverse method for airfoil design

Journal of Aircraft, 1995
This article presents an exact inverse method that generates the airfoil shape, satisfying all fluid dynamic and geometric constraints imposed by prescribing any input velocity distribution (or contour at the hodograph), with the only restriction that it does not take the same vector velocity at two different points of the boundary.
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Computer techniques for airfoil design

Mathematics and Computers in Simulation, 1976
Abstract This paper describes the application of the analogue solution of distributed parameter systems to the airfoil design problem. Conformal transformations are used to convert the boundary value problem, described by a laplacian field with exterior type of boundary conditions, to a set of initial value problems. The method is shown to render non-
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