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The Bagaliante is constructed from wood and metal and is of pod-and-boom layout. [1]The 12.2 m (40.0 ft) span wing employs a Göttingen 535 airfoil at the wing root, transitioning to an NACA 4412 section at the wingtip.
For example, the NACA 2412 airfoil has a maximum camber of 2% located 40% (0.4 chords) from the leading edge with a maximum thickness of 12% of the chord. The NACA 0015 airfoil is symmetrical, the 00 indicating that it has no camber. The 15 indicates that the airfoil has a 15% thickness to chord length ratio: it is 15% as thick as it is long.
The biplane wing employs a NACA 4412 airfoil. [2] [3] [4] The aircraft is towed behind a ski tow boat, lifting off at 35 mph (56 km/h) and climbing to about 200 ft (61 m), depending on the length of the tow rope used. The aircraft does not stall, but enters a nose-high mushing condition with a slow rate of descent. [3] [4]
NACA experience provided a model for World War II research, the postwar government laboratories, and NACA's successor, the National Aeronautics and Space Administration (NASA). NACA also participated in development of the first aircraft to fly to the "edge of space", North American's X-15. NACA airfoils are still used on modern aircraft.
The rear fuselage consists of two tubes, one above and one below the pusher engine. Its 10.7 m (35.1 ft) span wing employs a modified NACA 63-215 airfoil at the wing root transitioning to a NACA 4412 at the wing tips. The wing has an area of 14.2 m 2 (153 sq ft) and is supported by "V" struts.
PZL-Mielec, then known as WSK-Mielec, began to design the Dromader in the mid 1970s, with help of United States aircraft manufacturer Rockwell International.PZL-Mielec asked for Rockwell's help because of the political situation at the time: operating in an Eastern Bloc country, PZL wanted the aircraft to sell well worldwide, and the company realized that certification by the United States ...
Properties of Low-Aspect-Ratio Pointed Wings at Speeds Below and Above the Speed of Sound. NACA Report Nº 835, 1946; The Minimum Drag of Thin Wings in Frictionless Flow, Journal of the Aeronautical Sciences, Feb. 1951; Theoretical Determination of the Minimum Drag of Airfoils at Supersonic Speeds, Journal of the Aeronautical Sciences, Dec. 1952
Eastman Jacobs joined NACA in 1925 after earning a bachelor's degree in Electrical Engineering at the University of California, Berkeley. He applied at the Bell Labs but was not accepted and opted for his second choice Langley. His knowledge of complex analysis was key to current airfoil design techniques at the time. [1]