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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 profile was designed in 1922 by Virginius E. Clark using thickness distribution of the German-developed Goettingen 398 airfoil. [ 1 ]
Thin airfoil theory assumes the air is an inviscid fluid so does not account for the stall of the airfoil, which usually occurs at an angle of attack between 10° and 15° for typical airfoils. [20] In the mid-late 2000s, however, a theory predicting the onset of leading-edge stall was proposed by Wallace J. Morris II in his doctoral thesis. [ 21 ]
Vega 1. Five-seat cabin monoplane, accommodation for one pilot and four passengers, powered by a 225 hp (168 kW) Wright J-5, J-5A, J-5AB or J-5C Whirlwind radial piston engine. Vega 2. Five-seat cabin monoplane, powered by a 300 hp (220 kW) Wright J-6 Whirlwind radial piston engine. Vega 2A.
A: blue line = chord, green line = camber mean-line, B: leading-edge radius, C: xy coordinates for the profile geometry (chord = x axis; y axis line on that leading edge) The NACA airfoil series is a set of standardized airfoil shapes developed by this agency, which became widely used in the design of aircraft wings.
The General Aviation GA-43 was a single engine low-wing monoplane airliner produced in small numbers in the United States in the mid-1930s, also known as the Pilgrim 150, Fairchild 150, and sometimes but erroneously as the Clark GA-43 for the designer, Virginius E. Clark who was also responsible for the Clark Y airfoil section used.
Douglas received an order for nine single-engined transport aircraft in 1925, the first aircraft flying from Douglas's Santa Monica, California factory on 2 May 1925. [1] The C-1 was the first aircraft assigned in the new C- category. The aircraft design was based on several earlier and similar designs developed by Douglas in the early 1920s ...
The aerodynamic center is the point at which the pitching moment coefficient for the airfoil does not vary with lift coefficient (i.e. angle of attack), making analysis simpler. [1] where is the aircraft lift coefficient. The lift and drag forces can be applied at a single point, the center of pressure. However, the location of the center of ...
An actual model is built to a size suitable for the size of a specific wind tunnel test section, in particular taking care that the frontal blockage of the model (the ratio of the model cross-section area to wind tunnel test section area) is kept well below 1% (except for wall-interference research where the models may be larger).