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Accession Number:
AD0909874
Title:
Critical Mach Numbers of Circulation Control Airfoils as Determined by Finite-Difference Methods.
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
File Size:
0.00MB
