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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.
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 airfoil is a NACA laminar flow type of varying section over the span, starting at the wing root as a NACA 64(3)-618, becoming a NACA 64(3)-615 by mid-span and then a NACA 4412 at the tip. The wing is constructed from plywood and fiberglass and is responsible for the Annebula's performance increase from the Cherokee II's 23:1 glide ratio to ...
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 ...
Data from Plane and Pilot, Jane's all the World's Aircraft 1947, Stinson Operating Manual. General characteristics Crew: one Capacity: three passengers Length: 24 ft 6 in (7.46 m) Wingspan: 33 ft 11 in (10.33 m) Height: 6 ft 10 in (2.08 m) Wing area: 155 sq ft (14.4 m 2) Aspect ratio: 7.14 Airfoil: NACA 4412 Empty weight: 1,206 lb (547 kg) Gross weight: 2,150 lb (975 kg) Fuel capacity: 50 US ...
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Prior submerged inlet experiments showed poor pressure recovery due to the slow-moving boundary layer entering the inlet. The NACA design is believed to work because the combination of the gentle ramp angle and the curvature profile of the walls creates counter-rotating vortices which deflect the boundary layer away from the inlet and draws in the faster moving air, while avoiding the form ...