Parametric Study of a Plunging NACA0012 Airfoil
نویسندگان
چکیده
منابع مشابه
Unsteady flow past a plunging airfoil
This paper presents simulations of unsteady flow past a plunging airfoil using the highorder spectral difference (SD) method. Both third-order and fourth-order SD methods are used on unstructured quadrilateral grids. The vortex shedding pattern of an airfoil in an oscillating plunge motion becomes asymmetric at a sufficiently high frequency. The SD method is able to capture this effect and reve...
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A jet with a width of 2.5% the chord length is placed on a NACA0012 airfoil’s upper surface simulating the blowing and suction control under Re = 5 × 105 and angle-of-attack 18-deg conditions. Nearly 300 numerical simulations are conducted over a range of parameters (jet location, amplitude, and angle). The physical mechanisms that govern suction and blowing flow control are determined and anal...
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Abstract It is known that plunging airfoil can produce both lift and thrust with certain combination of plunging amplitude and frequency. Motivated by our interest in micro air vehicles (MAVs), we utilize a NavierStokes equation solver to investigate the aerodynamics of a flapping airfoil. The roles of the plunging and pitching amplitude and frequency, and Strouhal number are studied. For a sym...
متن کاملNumerical Study of the Aerodynamic Characteristics of a Plunging Rigid Airfoil with Elastic Trailing-Edge Plate
The fluid-structure coupling process of a plunging rigid airfoil with a thin elastic plate attached at the trailing-edge is simulated numerically by using unsteady potential flow source/vortex panel method and the Euler-Bernoulli beam vibration differential equation. The flow characteristics, the unsteady aerodynamic loads, especially the thrust effects of the plunging motion are computed. The ...
متن کاملPlunging 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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ژورنال
عنوان ژورنال: KnE Engineering
سال: 2020
ISSN: 2518-6841
DOI: 10.18502/keg.v5i6.7059