![]() Cars Īn inverted Clark Y airfoil was used on the spoilers of the Dodge Charger Daytona and Plymouth Superbird. Inexperienced modellers are more readily able to build model aircraft which provide a good flight performance with benign stalling characteristics. The Clark Y is appealing for its near-flat lower surface, which aids in the construction of wings on plans mounted on a flat construction board. Applications range from free-flight gliders through to multi-engined radio control scale models. ![]() The Clark Y has found favor for the construction of model aircraft, thanks to the flight performance that the section offers at medium Reynolds number airflows. The Clark Y was chosen as its flat bottom worked well with the design goal of a low radar cross-section. The Northrop Tacit Blue stealth technology demonstrator aircraft also used a Clark Y. Louis are two of the better known aircraft using the Clark Y profile, while the Ilyushin Il-2 and Hawker Hurricane are examples of mass-produced users of the Clark YH. Source UIUC Airfoil Coordinates Database (hor04-il) ONERA HOR04 AIRFOIL: Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file: Onera propeller blade airfoils from US Patent 4 Max thickness 4.1 at 33.2 chord Max camber 1.4 at 38. The Clark YH airfoil is similar but with a reflexed (turned up) trailing edge producing a more positive pitching moment reducing the horizontal tail load required to trim an aircraft. The flat lower surface is not optimal from an aerodynamic perspective, and it is rarely used in modern designs. ![]() ![]() The flat bottom simplifies angle measurements on propellers, and makes for easy construction of wings.įor many applications the Clark Y has been an adequate airfoil section it gives reasonable overall performance in respect of its lift-to-drag ratio, and has gentle and relatively benign stall characteristics. The airfoil has a thickness of 11.7 percent and is flat on the lower surface aft of 30 percent of chord. Clark using thickness distribution of the German-developed Goettingen 398 airfoil. The blade shape (airfoil contour) was obtained through an optimization study 1 that required a simple and fast estimation of propeller thrust and torque at a nominal Reynolds number of 300,000. The profile was designed in 1922 by Virginius E. © 2016 American Society of Civil Engineers.Clark Y is the name of a particular airfoil profile, widely used in general purpose aircraft designs, and much studied in aerodynamics over the years.The propellers were purchased off-the-shelf from retail outlets and were unmodified for these tests. This webpage includes wind tunnel measurements for nearly 140 propellers used on small UAVs and model aircraft. Find a library where document is available. This webpage compiled by Gavin Ananda, UIUC. From the first publication of data in 2005 through to 2022, the propeller database has grown to over 4 volumes of data and around 250 propellers tested over a range conditions.Excellent agreement between experiment and prediction is shown for subsonic helical tip Mach numbers. Results of this method are validated against experimental measurements. The proposed nonlinear airfoil model includes effects of angles of attack up to 90 degrees and compressibility corrections. The primary focus of this paper is on presenting a nonlinear aerodynamic model of airfoils that can be used in combination with the blade element method for enhanced propeller performance prediction over a wide range of advance ratios. This webpage compiled by Gavin Ananda, UIUC. The accuracy of the blade element method is, however, highly dependent on the fidelity of the airfoil aerodynamic model. An extensive literature survey reveals that for conventional high-aspect ratio propeller blades lifting surface and computational fluid dynamics approaches add a large degree of complexity without providing significantly improved performance prediction capabilities as compared to the blade element/vortex theory. Based on the validated process, a database of 22 commercial propellers from four companies is constructed containing all the reverse-engineered information. It executes rapidly on a personal computer and is capable of accurate propeller performance predictions. The blade element method is an indispensible engineering design tool. Integration of Airfoil Stall and Compressibility Models into a Propeller Blade Element Model
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