Accession Number:

AD0909874

Title:

Critical Mach Numbers of Circulation Control Airfoils as Determined by Finite-Difference Methods.

Descriptive Note:

Technical note,

Corporate Author:

DAVID W TAYLOR NAVAL SHIP RESEARCH AND DEVELOPMENT CENTER BETHESDA MD AVIATIO N AND SURFACE EFFECTS DEPT

Personal Author(s):

Report Date:

1972-08-01

Pagination or Media Count:

36.0

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

Subject Categories:

  • Helicopters
  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE