Accession Number:
ADA191408
Title:
An Integral Equation for the Linearized Supersonic Flow Over a Wing
Descriptive Note:
Interim rept. Nov 1986-Aug 1987
Corporate Author:
DAYTON UNIV OH RESEARCH INST
Personal Author(s):
Report Date:
1988-02-01
Pagination or Media Count:
102.0
Abstract:
In the first formulation. the integral equation for linearized steady supersonic flows appears in a form where it is necessary to approach the planform from above or below by a limiting process. In the present report, the problem is transformed analytically in such a manner that this limiting process no longer appears and that the resulting expressions are numerically tractable. It is believed that such a formulation gives more freedom to take the particularities of a given problem into account. The formulation is applied to compute the conical field which arises at the top of an airfoil. A possible numerical approach to the solution of the integral equation in the general case is described, but only in a rough outline.
Descriptors:
Subject Categories:
- Aerodynamics