A method for the aerodynamik optimization of three-dimensional configurations in supersonic flow (Q2734563)
From MaRDI portal
 | This is the item page for this Wikibase entity, intended for internal use and editing purposes. Please use this page instead for the normal view: A method for the aerodynamik optimization of three-dimensional configurations in supersonic flow |
scientific article; zbMATH DE number 1634665
| Language | Label | Description | Also known as |
|---|---|---|---|
| English | A method for the aerodynamik optimization of three-dimensional configurations in supersonic flow |
scientific article; zbMATH DE number 1634665 |
Statements
19 August 2001
0 references
three-dimensional configuration
0 references
supersonic flow
0 references
Euler equations
0 references
aerodynamic optimization
0 references
airfoil
0 references
airplane
0 references
Navier-Stokes equations
0 references
finite volume scheme
0 references
objective function
0 references
0.9059012
0 references
0 references
0.8928428
0 references
0.8804004
0 references
0.8719959
0 references
0.8692467
0 references
0.8687344
0 references
A method for the aerodynamik optimization of three-dimensional configurations in supersonic flow (English)
0 references
The dissertation is concerned with the optimization of airfoil and airplane configurations. The optimal criterion is based on a measure given by an objective function. The overall algorithm works as follows: at first, the flow field determined by the Euler or Navier-Stokes equations is simulated by means of a finite volume scheme. Thereafter, the geometry as well as the mesh are modified due to the values of the objective function employed. These two steps are repeated until the requirements associated with the objective function are perfectly satisfied. Several test cases are considered to emphasize the validity and efficiency of the method.
0 references
