| Article ID | Journal | Published Year | Pages | File Type |
|---|---|---|---|---|
| 791712 | Journal of Applied Mathematics and Mechanics | 2012 | 7 Pages |
Abstract
The problem of reducing the drag of a wing at a specified lift in a supersonic flow is investigated. A solution for a delta wing is obtained in a simplified formulation of the optimization problem and a theoretical analysis. It is shown that the optimal conical wing is formed by elements of elliptical cones and planes. Numerical modelling of the flow of a non-viscous non-heat-conducting gas past the wing is performed, and the results of the theoretical analysis and direct optimization are compared. ©2012
Related Topics
Physical Sciences and Engineering
Engineering
Mechanical Engineering
Authors
S.A. Takovitskii,