The Application of Green's Theorem to the Solution of Boundary-Value Problems in Linearized Supersonic Wing Theory
Abstract
Following the introduction of the linearized partial differential equation for nonsteady three-dimensional compressible flow, general methods of solution are given for the two and three dimensional steady-state and two-dimensional unsteady-state equations. It is also pointed out that, in the absence of thickness effects, linear theory yields solutions consistent with the assumptions made when applied to lifting-surface problems for swept-back plan forms at sonic speeds. The solutions of the particular equations are determined in all cases by means of Green's theorem and thus depend on the use of Green's equivalent layer of sources, sinks, and doublets. Improper integrals in the supersonic theory are treated by means of Hadamard's "finite part" technique.
Document Details
- Document Type
- Technical Report
- Publication Date
- Apr 01, 1949
- Accession Number
- ADA380869
Entities
People
- Harvard Lomax
- Max A. Heaslet
Organizations
- National Aeronautics and Space Administration