Accession Number : ADA184412
Title : The Use of Hot-Film Technique for Boundary Layer Studies on a 21% Thick Airfoil.
Descriptive Note : Aeronautical note,
Corporate Author : NATIONAL AERONAUTICAL ESTABLISHMENT OTTAWA (ONTARIO)
Personal Author(s) : Khalid,M
PDF Url : ADA184412
Report Date : May 1987
Pagination or Media Count : 54
Abstract : A heat transfer method of studying boundary layer flows over airfoils at transsonic test conditions has been investigated. The method employs very thin DISA hot-film gauges housing Constant Temperature Anemometer probes. Provided that the thickness dimension of the films remains less than the critical disturbances height for inducing transition of the laminar boundary layer, the heat transfer response from the films, positioned carefully on the model surface, can be studied to determine the boundary layer characteristics. Results from an application study on a 21% thick laminar flow airfoil model are presented and discussed.
Descriptors : *BOUNDARY LAYER FLOW, *BOUNDARY LAYER TRANSITION, *SUPERCRITICAL AIRFOILS, HOT WIRE ANEMOMETERS, FILMS, TRANSONIC CHARACTERISTICS, HEAT TRANSFER, DATA REDUCTION, GRAPHS, DRAG REDUCTION, REYNOLDS NUMBER, CANADA
Subject Categories : Fluid Mechanics
Distribution Statement : APPROVED FOR PUBLIC RELEASE