Accession Number:
AD0755762
Title:
Application of the Method of Integral Relations (MIR) to Transonic Airfoil Problems. Part 2. Inviscid Supercritical Flow About Lifting Airfoils with Embedded Shock Wave
Descriptive Note:
Corporate Author:
DAVID W TAYLOR NAVAL SHIP RESEARCH AND DEVELOPMENT CENTER BETHESDA MD AVIATION AND SURFACE EFFECTS DEPT
Personal Author(s):
Report Date:
1972-07-01
Pagination or Media Count:
79.0
Abstract:
Numerical procedures developed in a previous part of the report for applying the method of integral relations to transonic airfoil problems are extended to lifting cases. A modification enables any desired number of strips and size of integration domain to be used. Full inviscid flow equations are approximated by second-order polynomials in transverse direction in a physical plane. Numerical procedures including iterative processes are formulated for the case of high subsonic free-stream Mach numbers. Cartesian coordinates are employed except near the leading edge region where the use of a body coordinate system is convenient. Results are presented for supercritical flows past various airfoils, including two conventional, one advanced, and two shockless airfoils.
Descriptors:
Subject Categories:
- Aerodynamics
- Fluid Mechanics