An experimental study of the trailing edge flow of an NLR 7702 airfoil, using laser-doppler anemometry
article
Detailed measurements of mean flow and turbulence quantities have been performed in the vicinity of the trailing edge of a supercritical NLR 7702 airfoil using laser-Doppler anemometry (LDA). The two-dimensional (2-D) model, put at an angle of attack of 4°, was tested at a Reynolds number of 1.47 × 106. Under these conditions the upper surface boundary layer is close to separation at the trailing edge. Downstream of the trailing edge, both shear layers merge into a strongly curved, highly asymmetric near wake. Our main objective is to provide reliable experimental data for the development of turbulence closure models for trailing edge flows and to offer validation of computational methods. Besides the presentation of measured flow quantities, special attention is given to evaluate the accuracy and self-consistency of the data set obtained. © 1994.
Topics
ExperimentationTrailing edgesAirfoilsLasersDoppler effectVelocity measurementAerodynamicsTurbulent flowFluid dynamicsAerospace aerodynamicsLaser-Doppler measurementsTrailing edge flowsTurbulence modelingAirfoilsBoundary layersComputational methodsFlow measurementMathematical modelsPressure measurementSize determinationTurbulenceVelocity measurementWind tunnelsLaser Doppler anemometryReynolds numberTrailing edge flowAerofoilsAnemometers-Laser DopplerTrailing Edge Flow
TNO Identifier
123843
ISSN
0894-1777
Source
Experimental Thermal and Fluid Science, 9(2), pp. 174-185.
Pages
174-185
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