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A 6-bladed Hamilton Standard 568F propeller on an ATR 72 short-haul airliner. Lowry [27] quotes a propeller efficiency of about 73.5% at cruise for a Cessna 172.This is derived from his "Bootstrap approach" for analyzing the performance of light general aviation aircraft using fixed pitch or constant speed propellers.
Carburetor-equipped model with a thin wall front main bearing journal crankshaft, for a fixed pitch propeller, and a conical engine mount for a front propeller governor, that produces 180 hp (134 kW) at 2700 rpm, with a compression ratio of 8.5:1 and with a basic dry weight of 291 lb (132 kg). [2] O-360-B1A2
200 hp (149 kW) at 2700 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 8.70:1. Same as the A1A but uses a fixed-pitch propeller. [4] AIO-360-A2B 200 hp (149 kW) at 2700 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 8.70:1. Same as the A1A but has one impulse coupling magneto and provision for a fixed-pitch propeller.
The T-41B was the US Army version, with a 210 hp (160 kW) Continental IO-360 engine and constant-speed propeller in place of the 145 hp (108 kW) Continental O-300 and 7654 fixed-pitch propeller used in the 172 and the T-41A.
The DA40-F (marketed as the "FP") has a fixed pitch propeller, a 180 hp (130 kW) Lycoming O-360-A4M engine, which has a carburetor rather than fuel injection and a more basic interior, but is otherwise similar to the XL. [3] [4] The DA40-TDI uses a Thielert "Centurion" 135 hp (101 kW) diesel engine and burns diesel or jet fuel.
This engine was capable of running with a boost pressure of +9 lbs/sq.in (0.62 bar) and was first used in the Blenheim Mk IV. [1] The Mercury was also the first British aero engine to be approved for use with variable-pitch propellers. The Bristol company and its shadow factories produced 20,700 examples of the engine. [2]
The standard conversion installs a 230 hp (172 kW) Ford V6 powerplant, driving a fixed pitch propeller, although engines of up to 300 hp (224 kW) can be employed. The 230 hp (172 kW) engine gives the aircraft a sea level, standard day takeoff distance of 150 ft (46 m) and a landing distance of 300 ft (91 m). [1] [2]
Data from Jane's All the World's Aircraft 2010-11 General characteristics Crew: 1 Capacity: 3 pax Length: 6.61 m (21 ft 8 in) Wingspan: 8.6 m (28 ft 3 in) Height: 2.6 m (8 ft 6 in) Wing area: 11 m 2 (120 sq ft) Empty weight: 336 kg (741 lb) Max takeoff weight: 600 kg (1,323 lb) Max useful weight: 269 kg (593 lb) Powerplant: 1 × Rotax 912 ULS 4-cylinder air-cooled horizontally-opposed piston ...