Effects of Roughness on Advanced Airfoils PDF Download
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Author: Tezok, Fatih
Publisher: [Montréal] : The Centre
ISBN:
Category : Aerofoils
Languages : en
Pages : 274
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Book Description
Author: Tezok, Fatih
Publisher: [Montréal] : The Centre
ISBN:
Category : Aerofoils
Languages : en
Pages : 274
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Book Description
Author: Bombardier Aerospace
Publisher:
ISBN:
Category :
Languages : en
Pages : 136
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Book Description
Presents results of the second and third phases of a research program that studied the effects of roughness contamination on modern airfoils and wings. Phase two involved testing a Bombardier Aerospace proprietary supercritical airfoil section in a wind tunnel, and phase three involved a low-speed test of the Canadair Regional Jet wing in a larger wind tunnel. The performance of the tested models with different flap deflections, sweep angles, and roughness parameters was compared to computational fluid dynamics (CFD) results. A quasi-three-dimensional CFD model based on a viscous-inviscid coupling technique, using a panel method for the inviscid flow field and a two-dimensional compressible boundary layer with sweep and roughness effects, was calibrated using the results. Experimental results were also compared with Regional Jet flight test data. The results reveal the possibility of predicting the effects of roughness on aerodynamic performance.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Book Description
Author: Faith Tezok
Publisher:
ISBN:
Category :
Languages : en
Pages : 216
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Book Description
Author: Transport Canada. Safety and Security. Transportation Development Centre
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 137
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Book Description
Author: O. Schrenk
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 18
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Book Description
The first group of a large series of contemplated experiments on the effect of roughness was intended to show the effect of great roughness on airfoils of various sizes and attitudes.
Author: Laurence K. Loftin
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 48
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Book Description
Summary: Tests were conducted with two typical low-drag airfoils of 90-inch chord to determine the effects of surface projections, grooves, and sanding scratches on boundary-layer transition. The Reynolds number at which a spanwise row of cylindrical projections would cause premature transition was determined for a range of Reynolds number from approximately 3 x 106 to 10 x 106. Data were obtained for projections of various sizes and chordwise locations on both low-drag airfoils. The results were analyzed on the assumption that the critical airfoil Reynolds number for a given projection was a function only of the local-flow conditions around the projection. This assumption neglected possible effects of tunnel turbulence, pressure gradient, boundary-layer Reynolds number, and the original extent of the laminar flow. The data correlated on the basis of this assumption within a range of critical airfoil Reynolds number of ±0.5 x 106 and within a range of projection height of ±0.002 inch. The tests of surface grooves and sanding scratches indicated that, for the range of Reynolds number investigated, the laminar boundary layer was much less sensitive to surface grooves and sanding scratches than to projections above the surface.
Author: Frank T. Abbott
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 38
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Book Description
In connection with studies of airfoils applicable to large high-speed aircraft, the effects of roughness on three 22-percent-thick airfoils were investigated. The tests were made over a range of Reynolds numbers from about 6,000,000 to 26,000,000 for the airfoils smooth and with roughness strips applied to the surfaces. The results indicated that for the roughened models the scale effect was generally favorable.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 218
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Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 120
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Book Description
