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Experimental and Computational Studies of Dynamic Stall

  • L. W. Carr
  • M. F. Platzer
  • M. S. Chandrasekhara
  • J. Ekaterinaris

Abstract

The use and control of dynamic stall has become an important factor in both aircraft and helicopter design. At the present time, dynamic stall has limited, rather than enhanced, helicopter flight. At the same time, retention of the dynamic lift that occurs when aircraft rapidly pitch past the static stall angle is critical if the full benefit of this lift augmentation for improved aircraft maneuverability is to be achieved. Thus, the alleviation of unwanted aspects of dynamic lift, and the control and augmentation of the positive aspects of this dynamic lift condition, become major research goals.

Keywords

Mach Number Lift Coefficient Boundary Layer Equation Pitching Moment Inviscid Flow 
These keywords were added by machine and not by the authors. This process is experimental and the keywords may be updated as the learning algorithm improves.

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Copyright information

© Springer-Verlag Berlin Heidelberg 1990

Authors and Affiliations

  • L. W. Carr
    • 1
  • M. F. Platzer
    • 2
  • M. S. Chandrasekhara
    • 2
  • J. Ekaterinaris
    • 3
  1. 1.Aeroflightdynamics Directorate, U.S. Army ARTANASA Ames Research CenterMoffett FieldUSA
  2. 2.Navy-NASA Joint Institute of AeronauticsNaval Postgraduate SchoolMontereyUSA
  3. 3.Sterling Federal SystemsMountain ViewUSA

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