Comparison of Supersonic Minimum-Drag Airfoils Determined By Linear and Nonlinear Theory
Abstract
Supersonic profiles of minimum pressure drag for a given thickness ratio and for a given area have been determined with the use of a nonlinear pressure relation and are compared with minimum-drag profiles found by linearized theory. The results show that the profiles are determined with sufficient accuracy by linear theory over the entire supersonic Mach number range since the drag coefficients for these profiles are only slightly higher than those for optimum profiles determined by nonlinear theory. Linear theory appears to be adequate for determining profiles of minimum drag for other auxiliary structural conditions since moderate deviations from the optimum shape have only a small influence on the pressure drag.
Document Details
- Document Type
- Technical Report
- Publication Date
- Feb 01, 1952
- Accession Number
- ADA380591
Entities
People
- E. B. Klunker
- Keith C. Harder
Organizations
- National Aeronautics and Space Administration