Accession Number : ADA121598


Title :   An Experimental Study of Dynamic Stall on Advanced Airfoil Sections. Volume 2. Pressure and Force Data.


Descriptive Note : Technical memo.,


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


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


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/a121598.pdf


Report Date : Sep 1982


Pagination or Media Count : 646


Abstract : Experimentally derived force and moment data are presented for eight airfoil sections that were tested at fixed and varying incidence in a subsonic two-dimensional stream. Airfoil incidence was varied through sinusoidal oscillations in pitch over a wide range of amplitude and frequency. The surface pressure distribution, as well as the lift, drag, and pitching moment derived therefrom, are displayed in a uniform fashion to delineate the static and dynamic characteristics of each airfoil both in and out of stall. (Author)


Descriptors :   *ROTOR BLADES(ROTARY WINGS) , *STALLING , *SUPERCRITICAL AIRFOILS , PITCH(MOTION) , GRAPHS , HELICOPTER ROTORS , AIRFOILS , TABLES(DATA) , MACH NUMBER , TWO DIMENSIONAL FLOW , SUBSONIC FLOW , PRESSURE DISTRIBUTION , LIFT TO DRAG RATIO


Subject Categories : Helicopters
      Fluid Mechanics


Distribution Statement : APPROVED FOR PUBLIC RELEASE