This frequency was found by applying the solution to the Michalke spatial stability analysis to the experimental data. To mitigate the separation bubble, the electroactive polymers were actuated at a frequency corresponding to the Kelvin-Helmholtz instability of the separated mixing layer. Furthermore, the streamwise and cross-stream extents of the bubble decrease with the increase of the Reynolds number. A three-dimensional separation bubble was seen to exist when the airfoil's angle of attack was set at 5 deg, in agreement with the literature. In this study, flow control was accomplished through a row of surfacemounted electroactive polymers, centered at 20% of the airfoil chord. Naca-tn-734 Pressure Distribution Investigation of an NACA 0009 Airfoil with a 50% Chord Plain Flap and Three Tabs.Control of a laminar separation bubble on a two-dimensional NACA 0009 was investigated experimentally in an open-return wind tunnel using particle image velocimetry measurements at a range of chord-based Reynolds numbers Re C between 2.0 Naca-tn-734 Pressure Distribution Investigation of an NACA 0009 Airfoil with a 50% Chord Plain Flap and Three Tabs.pdf Moment coefficients were calculated for the flap with theĭifferent tabs and for the tabs alone. Lated for the airfoil section complete with the flap and Normal-force and pitching-moment coefficients were calcu» 0009 airfoil with aĥ0-percent-chord plain flap and with plain tabs 10, 20,Īnd 30 percent of the flap chord. The tests consisted of pressure-distribution measure~ Undertaken to supply information that would be applicableįor use in aerodynamic and structural design of tail sur. Namic characteristics of a thin airfoil as affected byįlaps and tabs. To tail~surface design, however, give the section aerody~ Plates, elevator nose shape, gap, and balance on the aero-ĭynamic characteristics of some tail surfaces of. The effects of such factors as plan form, outuouts, end (See refer-Įnces l and 2.) Previous investigations have indicated High control forces is the trailing-edge tab. Time, one of the most effective devices for reducing these The recent increases in speed and size of airplanes Tab sizes in reducing flap hinge moments decreased with The tests indicated that the effectiveness of all three Values computed by analytical methods are in good agree. Plots are also given of increments of utensi-įorce and hinge-moment coefficients for the airfoil, theįlap, and the three tabs. Grams for the airfoil with the flap and the 204percentejĬhord tab. The results are presented as resultant-pressure dia. May be applied to the design of horizontal and vertical The tests supplied aerodynamic section data that Tabs, having chords 10, 20, and 30 percent of the flapĬhord, were made in the N.A.G.A. 0009 air-įoil with a 50-percent-chord plain flap and three plain Pressure-distribution tests of an N.A.C.A. National Advisory Committee for Aeronautics, Technical Notes - Pressure Distribution Investigation of an NACA 0009 Airfoil with a 50% Chord Plain Flap and Three Tabs
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