Finite Element Analysis of Subsonic Transonic, and Supersonic Flows Around Missiles.
Abstract
This report examines the Galerkin finite element method for solving aerodynamics problems with emphasis on transonic flows. A shock element concept was proposed and computations were carried out. In this process, a quadratic isoparametric element is divided into quadrants with each quadrant having independent trial functions. This idea allows discontinuities at the center of an element and shocks are allowed to develop freely. Rankin-Hugoniot conditions are satisfied accurately. Although this method is efficient until freesteam Mach number reaches approximately 0.95, the solution seems to deteriorate significantly for M > 0.95. Toward the end of the reporting period, the author proposed a new approach--optimal control penalty finite elements. This method is suited ideally for problems of discontinuity and shock waves as a consequence of changes in the type of partial differential equations. The resulting equations are symmetric and positive-definite, their solution being type-idependent. Numerous examples indicate that both stability and accuracy are maintained very satisfactorily for Tricomi and small perturbation equations. Detailed calculations applied to the full potential equations using this approach are beyond the scope of the present study.
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 01, 1979
- Accession Number
- ADA077375
Entities
People
- T. J. Chung
Organizations
- University of Alabama in Huntsville