Accession Number : ADA119827

Title :   An Experimental Study of Dynamic Stall on Advanced Airfoil Sections. Volume 1. Summary of the Experiment.

Descriptive Note : Technical memo.,

Corporate Author : NATIONAL AERONUATICS AND SPACE ADMINISTRATION MOFFETT FIELD CA AMES RESEARCH CENTER

Personal Author(s) : McCroskey,W J ; McAlister,K W ; Carr,L W ; Pucci,S L

PDF Url : ADA119827

Report Date : Jul 1982

Pagination or Media Count : 102

Abstract : The static and dynamic characteristics of seven helicopter sections and a fixed-wing supercritical airfoil were investigated over a wide range of nominally two-dimensional flow conditions, at Mach numbers up to 0.30 and Reynolds numbers up to 4x10 to the 6th power. Details of the experiment, estimates of measurement accuracy, and test conditions are described in this volume. The results of the experiment show important differences between airfoils, which would otherwise tend to be masked by differences in wind tunnels, particularly in steady cases. All of the airfoils tested provide significant advantages over the conventional NACA 0012 profile. In general, however, the parameters of the unsteady motion appear to be more important than airfoil shape in determining the dynamic-stall airloads.

Descriptors :   *Supercritical airfoils, *Rotor blades(Rotary wings), *Stalling, Airfoils, Boundary layer flow, Unsteady flow, Pressure Distribution, Oscillation, Lifting surfaces, Pitch(Inclination), Drag, Static tests, Helicopters

Subject Categories : Helicopters
      Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE