Aeroacoustic analysis of an airfoil with Gurney flap based on time-resolved particle image velocimetry measurements
نویسندگان
چکیده
منابع مشابه
Plunging Airfoil Load Characteristics Equipped with Gurney Flap
Numerous experiments have been conducted on plunging Eppler 361 airfoil in a subsonic wind tunnel. The experimental tests involved measuring the surface pressure distribution over the airfoil at Re=1.5×105. The airfoil was equipped with Gurney flap(heights of 2.6, 3.3 and 5% chord) and plunged at 6cm amplitude. The unsteady aerodynamic loads were calculated from the surface pressure measurement...
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The problem investigated in this experiment was which height of Gurney Flap gives the best lift improvement on an airfoil without increasing drag. The Gurney Flaps' heights are determined as a percentage of the airfoil's chord length. The hypothesis is that a Gurney Flap will produce the best lift to drag ratio when its height is two percent of the airfoil's chord length. The hypothesis was tes...
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The flow field in an acoustic standing wave tube was measured using time-resolved particle image velocimetry (PIV). Verifications were made through comparisons between measured and predicted acoustic particle velocities in the spatial domain and the time domain. The accuracy of the time-resolved PIV system was satisfactory, at least for the periodic flow velocity component. The steady streaming...
متن کاملComputational Investigations on the Effects of Gurney Flap on Airfoil Aerodynamics
The present study comprises steady state, two-dimensional computational investigations performed on NACA 0012 airfoil to analyze the effect of Gurney flap (GF) on airfoil aerodynamics using k-ε RNG turbulence model of FLUENT. Airfoil with GF is analyzed for six different heights from 0.5% to 4% of the chord length, seven positions from 0% to 20% of the chord length from the trailing edge, and s...
متن کاملFlap Edge Aeroacoustic Measurements and Predictions
An aeroacoustic model test has been conducted to investigate the mechanisms of sound generation on high-lift wing configurations. This paper presents an analysis of flap side-edge noise, which is often the most dominant source. A model of a main element wing section with a half-span flap was tested at low speeds of up to a Mach number of 0.17, corresponding to a wing chord Reynolds number of ap...
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ژورنال
عنوان ژورنال: Journal of Sound and Vibration
سال: 2018
ISSN: 0022-460X
DOI: 10.1016/j.jsv.2018.02.039