![]() The results notably disclosed a remarkable 41% increase in maximum lift-to-drag ratio attained with a Gurney flap of 2% chord length. They found that the Gurney flap significantly improved the aerodynamic performance of the airfoil. 13–15 embarked upon a detailed examination of the influence of Gurney flaps on the aerodynamic characteristics of the NACA 0012 airfoil at Ma = 0.7. Liebeck 12 evidenced the consequential enhancement in lift coefficient due to the Gurney flap but also revealed a proportional rise in drag when flap heights surpassed 2% of chord length. The findings underscored the potency of 5% and 7% Gurney flaps in enhancing the airfoil’s aerodynamic behavior. They considered three distinct Kn numbers (0.026, 0.1, 0.26), three variable Gurney flap heights (2%, 5%, 7%), and a wide range of AOA. 11 investigated the impacts of AOA and Gurney flap height on the aerodynamic performance of the NACA 0012 airfoil within the domain of rarefied conditions. Hence, the necessity to enhance the aerodynamic performance of airfoils in rarefied gas flow has become palpable.Īs a simple and low-cost method, the Gurney flap is often used to enhance the aerodynamic attributes of airfoils. 2,6–8 They illuminated the direct correspondence between an augmented Knudsen number and an augmented drag coefficient, ultimately resulting in the deterioration of aerodynamic performance. Recently, researchers began to investigate the flow field simulation surrounding airfoils operating within rarefied gas flow conditions by using the Direct Simulation Monte Carlo (DSMC) method. 2 During the preceding decades, researchers have studied the aerodynamic characteristics of small-size wings by wind tunnel test and CFD method 3–5 and obtained many valuable conclusions. 1 Notably, prevalent MAVs are scaled-down renditions of traditional aircraft with chords spanning mere centimeters, once the characteristic scale is sufficiently small, the non-equilibrium, rarefied flow phenomenon becomes dominant. The aerodynamic attributes of MAVs have constituted a focal point for numerous researchers. The micro air vehicle (MAV) has attracted substantial attention in contemporary times due to its potential to perform various missions and low production cost compared with full-size aircraft. The results show that through optimization, the lift-to-drag ratio of the airfoil is increased by up to 29.25% under the combination of different Mach numbers and Knudsen numbers, which significantly improves the aerodynamic characteristics. Based on the benchmark configuration (obtained from the Pareto front), aerodynamic optimization by controlling the mounting angle of the Gurney flap and the angle of attack is investigated over a wide range of Mach numbers (ranging from 2 to 4) and Knudsen numbers (ranging from 0.024 to 0.24) by constructing an artificial neural network model. ![]() Furthermore, the multi-objective aerodynamic optimization of the airfoil with Gurney flap is performed at the single design point, and the Pareto front is obtained. ![]() In order to investigate the effects of Gurney flap geometry (height, mounting angle, and mounting location) and angle of attack on the aerodynamic characteristics of the airfoil in the rarefied gas flow, the flow fields around NACA 0012 airfoils with Gurney flap attached are simulated by using the direct simulation Monte Carlo method. Welcome to, a database of shapes, data, and other information pertinent to 2D airfoil sections.The aerodynamic optimization of a Gurney flap attached to the NACA 0012 airfoil in rarefied gas flow is studied in this study. Various links to airfoils management websites Serge Barth, Sergey Sobakin, Stéphane Combet, S andere NACA (Verwirklichen Sie Ihre Naca-Profile), NM, MVR et NMR ( Nicolas Mathis+Marco Virgilio Ricci) Marcel Guwang, Matthieu Scherrer, Martin Hepperle, E. Hannes Delago, HL B.Horeni et J.Lnenka,Hans Meyer, Hammarskiöld-Mattias, Norbert Habe, Horten,Helmut Quabeck, Hartmut Siegmann, H andere ![]() ![]() + For other airfoils files, consult the " Free Pack Airfoils".ĭownload All the airfoils from these pages - 850 Ko ()ĭirk Pflug, Mark Drela, Delft University, DS airfoil(Joe WURTS) Profildatenbank Die untenstehenden Profile sind *.dat und *.cor.ĭiese Profile sind in der UIUC Airfoil Data Site nicht enthalten and are into the " Free Pack Airfoils" A commercial use is restricted by the designers copyright, Please contact the designer. The airfoils can be used by every private person. ![]()
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