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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 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.
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.
Data from Jane's All the World's Aircraft 1969–70 General characteristics Crew: one Capacity: one passenger Length: 22 ft 8 in (6.91 m) Wingspan: 33 ft 5 in (10.19 m) Height: 6 ft 7 + 3 ⁄ 4 in (2.03 m) Wing area: 165 sq ft (15.3 m 2) Aspect ratio: 6.72:1 Airfoil: NACA 4412 Empty weight: 1,037 lb (470 kg) Gross weight: 1,650 lb (748 kg) Fuel capacity: 39 US gal (32 imp gal; 150 L ...
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Airfoil: NACA 4412 [3] Empty weight: 1,280 lb (581 kg) Gross weight: 2,280 lb (1,034 kg) Fuel capacity: 42 US gal (35 imp gal; 160 L) Powerplant: 1 × Continental E165 6-cylinder air-cooled horizontally-opposed piston engine, 165 hp (123 kW) Propellers: 2-bladed Sensenich or Lewis fixed-pitch propeller; Performance
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]