Limit cycle torsional motion of helicopter blades due to stall-Reference-Cited by-同舟云学术

Limit cycle torsional motion of helicopter blades due to stall

Published:1966-11 Issue:3 Volume:4 Page:431-444
ISSN:0022-460X
Container-title:Journal of Sound and Vibration
language:en
Short-container-title:Journal of Sound and Vibration

Author:

Ham N.D.,Young M.I.

Publisher

Elsevier BV

Subject

Mechanical Engineering,Mechanics of Materials,Acoustics and Ultrasonics,Condensed Matter Physics

Reference7 articles.

1. An experimental investigation of stall flutter;Ham;J. Am. Helicopter Soc.,1962

2. Single degree of freedom flutter of compressor blades in separated flow;Schnittger;J. aeronaut. Sci.,1954

3. NACA TN 2533;Halfman,1951

4. NACA TN 3622;Rainey;Preliminary study of some factors which affect the stallflutter characteristics of thin wings,1956

5. NACA Tech. Report TR 1305;Rainey;Measurement of aerodynamic forces for various mean angles of attack on an airfoil oscillating in pitch, etc., with emphasis on damping in the stall,1957

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