Review of MIT Research on Airfoil Dynamics Stall 1964 - 1971.

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Abstract:

Research on the dynamic stall of airfoils and helicopter blades is described, beginning with wind tunnel tests and helicopter flight tests which led to the current research. Flutter criteria, tests of two-dimensional airfoils undergoing large transient motions, and a partial theory of airfoil dynamic stall are presented. The application of the two-dimensional results to the loading and motion of rotor blades due to stall is described. Unsteady boundary layer analyses and tests, and their relationship to the development of a complete flow separation model, to airfoil design, and to blade-vortex interaction effects are summarized.

Author(s):
Ham, Norman D.
Author Organization(s):
MASSACHUSETTS INST OF TECH CAMBRIDGE AEROELASTIC AND STRUCTURES RESEARCH LAB
Descriptive Note:
Technical rept.,
Pagination:
0033

Security Markings

DOCUMENT & CONTEXTUAL SUMMARY

Distribution:
Approved For Public Release

RECORD

Collection: TR
Identifying Numbers
Report Number(s):
ASRL-TR-130-3, AROD-4846:13-E
Contract/Grant Number(s):
DA-31-124-ARO(D)-247
Monitor Series:
4846:13-E
 Subject Terms
Communities of Interest:
No COI(s) Identified
Descriptor(s):
(*AIRFOILS, STALLING), (*ROTOR BLADES(ROTARY WINGS), STALLING), AIRFOILS, THEORY, WIND TUNNEL MODELS, TWO DIMENSIONAL FLOW, DYNAMICS, BOUNDARY LAYER, VORTICES, INTERACTIONS, FLIGHT TESTING, HELICOPTER ROTORS, FLOW SEPARATION, MATHEMATICAL MODELS
Field(s)/Group(s):
Aerodynamics, Fluid Mechanics
Keyword(s):
UNSTEADY FLOW
Report Date:
1971 Sep 01