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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.
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 root airfoil, a NACA 0015 on other models of the P-39, was changed to a NACA 0018, to gain internal volume. [2] The other was a switch to the Continental I-1430 engine, which featured an improved overall design developed from the hyper engine efforts, as well as an improved supercharger.
Max M. Munk, chief of aerodynamics, in his office at Langley, 1926. Max Michael Munk (October 22, 1890 – June 3, 1986) [1] was a German aerospace engineer who worked for the National Advisory Committee for Aeronautics (NACA) in the 1920s and made contributions to the design of airfoils.
Airfoil: NACA 0015; Empty weight: 750 lb (340 kg) Max takeoff weight: 1,200 lb (544 kg) Powerplant: 1 × RotorWay RW133 4-cylinder horizontally opposed liquid-cooled piston engine, 133 [4] hp (99 kW) Main rotor area: 452 sq ft (42.1 m 2) two blade semi-rigid rotor; Performance. Cruise speed: 78 kn (90 mph, 145 km/h) Range: 104 nmi (120 mi, 193 km)
Data from Jane's All the World's Aircraft 1992-93 General characteristics Crew: 1 Length: 20 ft 3 in (6.17 m) Wingspan: 20 ft 2 in (6.15 m) Height: 5 ft 5 in (1.65 m) Wing area: 85 sq ft (7.9 m 2) Airfoil: NACA 0015 Empty weight: 800 lb (363 kg) Max takeoff weight: 1,150 lb (522 kg) Fuel capacity: 27 imp gal (32 US gal; 120 L) in two fuselage tanks Powerplant: 1 × Textron Lycoming IO-360 4 ...
Airfoil: NACA 0015; Empty weight: 225 lb (102 kg) Gross weight: 550 lb (249 kg) Max takeoff weight: 590 lb (268 kg) maximum crew weight with maximum fuel; Fuel capacity: 20 US gal (17 imp gal; 76 L) / 125 lb (57 kg) Compressor: Pesco engine driven compressor; Compressor capacity: 27 cu ft/min (765 L/min) Inflation pressure: 7 psi (48.26 kPa)
Its 33 ft (10.1 m) diameter fully articulated three-bladed main rotor employs a NACA 0015 airfoil. [4] The two-bladed tail rotor has a diameter of 5.75 ft (1.8 m). The aircraft has an empty weight of 1,790 lb (812 kg) and a gross weight of 2,800 lb (1,270 kg), giving a useful load of 1,010 lb (458 kg).