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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.
A combination of the then new NACA profiles used gave the wing more camber at the tip. Since higher camber airfoils stall at greater angles of attack measured from the zero-lift line , the combination of higher camber and washout means that the stall develops inboard and that the ailerons, on the unstalled outer wing, retain lateral control and ...
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 Jane's All The World's Aircraft 1982–83 General characteristics Crew: 1 Length: 18 ft 0 in (5.49 m) Wingspan: 24 ft 0 in (7.32 m) Height: 5 ft 1.5 in (1.562 m) Wing area: 100 sq ft (9.3 m 2) Airfoil: NACA 4412 Empty weight: 440 lb (200 kg) Max takeoff weight: 750 lb (340 kg) Powerplant: 1 × Volkswagen 4-cylinder air-cooled horizontally-opposed piston engine, 40 hp (30 kW ...
Designed by H. Friedmann. First flight 1937. Aerofoil: NACA 4415 to NACA 4412 20 m (65 ft 7 in), Wing area 20 m2 (220 sq ft), Empty wt. 180 kg (400 lb) No. of seats 2. 0 built. A projected two-seater similar to the D-30 Cirrus, with a pod and boom fuselage and wings of lower aspect ratio.
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 ...
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