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Type MTOW [kg] MLW [tonnes] TOR [m] LR [m] ICAO category FAA category; Antonov An-225: 640,000: 591.7: 3,500: Super: Super Scaled Composites Model 351 Stratolaunch
The experiment precedes the X-57 Maxwell X-plane demonstrator proposed under NASA's Transformative Aeronautics Concepts program. A piloted X-plane should fly within a couple of years, after replacing a Tecnam P2006T wings and engines with an improved version of the LEAPTech wing and motors. Using an existing airframe will allow engineers to ...
The conversion cost $1.9 million in 2009, resulting in a $3.5-4.6 million value for a converted Citation II. [18] Ceiling is increased from FL 410 to FL 430, reached directly in 25 min at max takeoff weight with a thrust increased from 2,500 to 2,820 lbf (11.1 to 12.5 kN) each. [18]
Its FJ44 engine has a 16:1 overall pressure ratio and a 2.58:1 bypass ratio. [ 8 ] [ 11 ] Early CitationJet models have a novel design feature to reduce weight: rather than conventional thrust reversers , the aircraft are equipped with thrust attenuator paddles that pivot from the rear fuselage, similar to those used on the Cessna T-37 Tweet ...
For aircraft specification calculation in aeronautics, limit load (LL) is the maximum design load expected as the maximum load any aircraft will see during its lifetime, [1] The limit load can be found relatively easily by statistically analysing the data collected during the many hours of logged flights (which is continuously being gathered ...
The amount a weight must be moved can be found by using the following formula shift distance = (total weight * cg change) / weight shifted Example: 1500 lb * 33.9 in = 50,850 moment (airplane) 100 lb * 68 in = 8,400 moment (baggage) cg = 37 in = (50,850 + 8,400) / 1600 lb (1/2 in out of cg limit)
Data from Jane's all the world's aircraft 1976–77. General characteristics Crew: Two Capacity: four passengers Length: 36 ft 9.75 in (11.22 m) Wingspan: 49 ft 0.5 in (14.95 m) Height: 14 ft 6 in (4.42 m) Wing area: 255 sq ft (23.69 m 2) Aspect ratio: 9.45:1 Airfoil: NACA 23012 modified Empty weight: 4,635 lb (2,102 kg) Max takeoff weight: 6,750 lb (3,062 kg) Powerplant: 2 × Lycoming IO-540 ...
The logarithmic term with weight ratios is replaced by the direct ratio between / = where is the energy per mass of the battery (e.g. 150-200 Wh/kg for Li-ion batteries), the total efficiency (typically 0.7-0.8 for batteries, motor, gearbox and propeller), / lift over drag (typically around 18), and the weight ratio / typically around 0.3.