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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
A sample CG-moment envelope chart, showing that a loaded plane weighing 2,367 lb (1,074 kg) with a moment of 105,200 lb⋅in (11886 N⋅m) is within the "normal category" envelope. Center of gravity (CG) is calculated as follows: Determine weights and arms for all mass within the aircraft. Multiply weights by arms for all mass to calculate moments.
The aircraft gross weight (also known as the all-up weight and abbreviated AUW) is the total aircraft weight at any moment during the flight or ground operation. [ 1 ] [ 2 ] [ 3 ] An aircraft's gross weight will decrease during a flight due to fuel and oil consumption.
Rocketdyne RS-25 rocket engine [9] 3,177 7,004 2,278 512,000 73.1 RD-180 rocket engine [10] 5,393 11,890 4,152 933,000 78.5 RD-170 rocket engine 9,750 21,500 7,887 1,773,000 82.5 F-1 (Saturn V first stage) [11] 8,391 18,499 7,740.5 1,740,100 94.1 NK-33 rocket engine [12] 1,222 2,694 1,638 368,000 136.7 Merlin 1D rocket engine, full-thrust ...
Aircraft engine performance refers to factors including thrust or shaft power for fuel consumed, weight, cost, outside dimensions and life. It includes meeting regulated environmental limits which apply to emissions of noise and chemical pollutants, and regulated safety aspects which require a design that can safely tolerate environmental hazards such as birds, rain, hail and icing conditions.
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.
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]
For supersonic flight, drag increases at Mach 1.0 but decreases again after the transition. With a specifically designed aircraft, such as the (discontinued) Aerion AS2, the Mach 1.1 range at 3,700 nmi is 70% of the maximum range of 5,300 nmi at Mach 0.95, but increases to 4,750 nmi at Mach 1.4 for 90% before falling again. [6]