The cirrus sr22 is a single-engine four- or five-seat composite aircraft built from 2001 by cirrus aircraft of duluth, minnesota.
It is a development of the cirrus sr20, with a larger wing, higher fuel capacity, and a more powerful, 310-horsepower (231 kw) engine.
The sr22 has been the world's best-selling general aviation (ga) airplane every year since 2002. It is the most-produced ga aircraft made from composite material, accounting for over 30% of the entire piston aircraft market
General characteristics
Crew: one
Capacity: four passengers
Length: 26 ft 0 in (7.92 m)
Wingspan: 38 ft 4 in (11.68 m)
Height: 8 ft 11 in (2.72 m)
Airfoil: roncz
Empty weight: 2, 225 lb (1, 009 kg)
Gross weight: 3, 600 lb (1, 633 kg)
Fuel capacity: 92 us gallons (348 litres)
Powerplant: 1 continental io-550-n six cylinder horizontally opposed aircraft engine, 310 hp (230 kw)
Propellers: 3-bladed
Performance
Cruise speed: 183 kn (211 mph; 339 km/h)
Stall speed: 60 kn (69 mph; 111 km/h) flaps down
Range: 1, 049 nmi (1, 207 mi; 1, 943 km) with reserves at 65% power
Service ceiling: 17, 500 ft (5, 300 m)
Rate of climb: 1, 270 ft/min (6.5 m/s)
The robinson r22 is a two-bladed, single-engine light utility helicopter manufactured by robinson helicopter company. The two-seat r22 was designed in 1973 by frank robinson and has been in production since 1979.
General characteristics
Crew: 1
Capacity: 2, including pilot
Length: 28 ft 8 in (8.74 m)
Rotor diameter: 25 ft 2.4 in (7.67 m)
Tail rotor diameter: 3 ft 6 in (1.07 m)
Height: 8 ft 11 in (2.72 m)
Disc area: 497 (46.2 m)
Empty weight: 880 lb (399 kg[23])
Loaded weight: 920 lb (417 kg)
Max. Takeoff weight: 1, 370 lb (635 kg)
Main tank total capacity: 19.8 us gallons (75 liters)
Main tank usable capacity: 19.2 us gallons (73 liters)
Optional aux tank total capacity: 10.9 us gallons (41 liters)
Optional aux tank usable capacity: 10.5 us gallons (40 liters)
Powerplant: 1 ã? lycoming o-320-a2b or -a2c flat 4 piston engine, 124 hp (93 kw)
Performance
Never exceed speed: 117 mph, 188 km/h, 102 kts
Cruise speed: 110 mph, 177 km/h, 96 kts
Range: 240 mi (386 km)
Service ceiling: 14, 000 ft (4, 267 m)
Rate of climb: 1, 200 ft/min (6.1 m/s)
Disc loading: 2.61 lb/ (13.7 kg/m)
Fuel consumption: 8~10 us gal/hr
Power/mass: 0.095 hp/lb (0.147 kw/kg)
Endurance: approx. 3 hours, with 30-minute reserve
The cessna citation mustang, model 510, is a very light jet (vlj) class business jet built by cessna aircraft company at their independence, kansas production facility. The mustang, in standard configuration, has four passenger seats in the aft cabin, a toilet, and seating for two in the cockpit. Like most other light jets, the mustang is approved for single-pilot operation.
General characteristics
Crew: one or two pilots
Capacity: 4 to 5 passengers
Length: 40 feet 7 inches (12.37 m)
Wingspan: 43 feet 2 inches (13.16 m)
Height: 13 feet 5 inches (4.09 m)
Empty weight: 5600 lb (2540 kg)
Useful load: 3130 lb (1420 kg)
Max. Takeoff weight: 8645 lb (3930 kg)
Powerplant: 2 pratt & whitney canada pw615f turbofans, 1460 lb thrust (6.49 kn) each
Performance
Maximum speed: mach 0.63 (483 mph, 777 km/h)
Cruise speed: 340 ktas (390 mph, 630 km/h)
Range: 1167 nmi (at max. Takeoff weight) (1, 343 mi, 2, 161 km)
Service ceiling: 41000 ft (12500 m)
Rate of climb: 3010 fpm (917 mpm)
Thrust/weight: 0.337 (at max. Takeoff weight)
Takeoff distance: 3, 110 ft (948 m)
Landing distance: 2, 380 ft (729 m)
Aviation Jet Fuel is a type of aviation fuel designed for use in aircraft powered by gas-turbine engines. It is colourless to straw coloured in appearance. The most commonly used fuels for commercial aviation are Jet A and Jet A1, which are produced to a standardised international specification. The only other jet fuel commonly used in civilian turbine-engine powered aviation is Jet B, which is used for its enhanced cold-weather performance.
Jet fuel is a mixture of a variety of hydrocarbons. Because the exact composition of jet fuel varies widely based on petroleum source, it is impossible to define jet fuel as a ratio of specific hydrocarbons. Jet fuel is therefore defined as a performance specification rather than a chemical compound.
Aviation Jet Fuel is commonly referred to as JP54. However, this is the wrong terminology as there is no such grade of Jet Fuel. Jet A and Jet A1 are what refineries offer. Aviation Jet fuel Gas is what powers turbine aircraft engines. Worldwide, Jet Fuel is the most used low Sulphur content Kerosene. For instance, Colonial JP54 is similar to Jet A except the energy is 18.4 mj/Kg compared to the 42.8 MJ/kg of Jet A. Most importantly there is also a slight difference in additives.
Aviation Jet Fuel B is used for its extremely cold weather performance. However, aviation Jet fuel Bs lighter composition makes it more dangerous to handle. For this reason, it is rarely used except in very cold climates. A blend of approximately 30% Kerosene and 70% Gasoline. Because of its very low freezing point (60 C (76 F), it is known as a wide cut fuel and has a low flash point as well. Aviation Jet Fuel B is primarily used in some military aircraft. In Canada, it is also used because of its freezing point. Aviation Kerosene standards are published as GOST10227-86. The standard consists of different properties. It separates paraffin and gasoline in the refinery.
Military organisations around the world use a different classification system of JP (for Jet Propellant) numbers. Some are almost identical to their civilian counterparts and differ only by the amounts of a few additives. For instance, Jet A1 is similar to JP 8, Jet B is similar to JP 4. Military fuels are highly specialised products and are developed for very specific applications. Jet fuels are sometimes classified as kerosene or naphtha type. Kerosene type fuels include Jet A, Jet A1, JP 5 and JP 8. Naphthatype jet fuels, sometimes referred to as wide cut Jet Fuel, including Jet B and JP 4.
A new ANG 01 aircraft has been designed and manufactured in 2019. ANG 01 is based on the concept of LA-50 aircraft, At the same time, ANG 01 is substantially more perfect than its predecessor. Thus, due the use of new carbon fiber materials, its weight was reduced and its strength characteristics were enhanced.
Owing to the usage of specialized computer programs, the company specialists have managed to implement an optimum structure of the fuselage and wing, having achieved hereby their best performance. We have also used the advanced products for computer-based wind-tunnel simulation that allows modeling the characteristics of the airframe and fine-tuning them at the development phase.
The development of the aircraft was performed, based on the latest technological achievements, with the use of the up-to-date CAD systems for aircraft design computing, which allowed to carry out the design strength aerodynamics testing, etc. with high precision directly in the computer. Due to the calculations solely in CAD systems, we have obtained the aircraft empty weight of 380-400 kg (maximum configuration), while the maximum take-off weight is of 950 kg. Thus, the payload is 550-570 kg, that is 137%-150% of its own weight.
Besides, to enhance the safety of the aircraft, it was equipped with a modern parachute rescue system GRS 6 800-990 SDS manufactured by the Czech company Galaxy GRS s.r.o.
Reliability and ease of control is provided by modern electronic SkyView HDX system manufactured by Dynon Avionics.
Specifications
Number of Seats 5
Engine Rotax 915 iS3A 141 HP
fuel Type Avgas A-92, A-95, A-98, 100LL
Propeller 3 blade, Variable Pitch Type
Landing Gear trycicle type, hydraulically retractable
Maximum Takeoff Weight 950 kg
empty weight 380 kg
The capacityof fuel tanks 245 l
wing area 11,3 m2
Wingspan 9,6 m
Aircraft Length 7,138 m
Height 2,65 m
fuselage width MAX 1,35 m
cabin height 1,2 m
Cabin length MAX 2.3 m
Wing loading 84 kg/m2
Landing Gear Tread 1.9 m
wheel size 8â?? (420 mm)
Luggage Compartment Capacity 780 liters
Maximum Lift-to-Drag Ratio 18.6
Max speed 360 km/h
Maximum cruising speed 345 km/h
Cruising speed 85% 310 km/h
landing speed 70 km/h
Cruising speed 65% 290 km/h
rate of climb 3,5 m/s
Takeoff Run 300 m
Landing Roll 150 m
at an altitude of 4000m Climb rate 8.3m / sec
