Critical Mach Numbers of Circulation Control Airfoils as Determined by Finite-Difference Methods.
Abstract
The critical Mach number of several circulation control elliptic airfoils is calculated for various circulation and angle-of-attack conditions. The full inviscid compressible flow equations were solved by finite-difference relaxation methods. The sections examined are candidates for use on helicopter rotor blades. Comparison with conventional sections are made. It is shown that the elliptic circulation control airfoils have a significantly higher critical Mach number. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Aug 01, 1972
- Accession Number
- AD0909874
Entities
People
- David W Taylor
- Ernest O. Rogers