Accession Number:

AD0909874

Title:

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

Personal Author(s):

Corporate Author:

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

Report Date:

1972-08-01

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

Descriptive Note:

Technical note,

Pages:

0036

Subject Categories:

File Size:

0.00MB

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