Small piston propeller aircraft Cirrus SR-20 aircraft is a small piston propeller aircraft produced by Cirrus Aircraft Design and Manufacturing Company, with a lower wing design, the fuselage is made of composite materials, and the whole aircraft can carry 4 people. Equipped with a Garmin Perspective avionics system, the navigation equipment is advanced. The control device is a control side rod that connects each control surface through a steel cable, and the trim is realized by an electric motor. It is a small aircraft that is highly electric. It has a unique complete parachute system (CAPS), which can ensure the life safety of the crew in an emergency. In 1998, it obtained FAA airworthiness standards. Suitable for use as a private jet as well as a junior trainer aircraft. In 2011, the Civil Aviation Flight University of China introduced this aircraft as a flight training aircraft and served in the Luoyang Branch of the Civil Aviation Flight University of China. At 3:07 p.m. on May 15, 2024, the color-painted Cirrus SR20 aircraft successfully flew at Jimo Airport. [8] The Chinese name is Xirui SR-20 Foreign name Cirrus SR-20 Manufacturer: Cirrus Aircraft Design & Manufacture Company Aircraft Category: Single-Engine Normal Class Engine type: Six-cylinder horizontally opposed direct-injection piston engine Engine manufacturer Tridyne Continental Rated horsepower 200 horsepower The rated speed is 2700RPM Propeller manufacturer Hartzell Fuel 100 100LL aviation gasoline is used Total fuel capacity 58.5 gal Usable fuel capacity 56 gallons Maximum take-off weight 1383 kg The maximum landing weight is 1383 kg
Overview Engine: Tridyne Continental IO-360-ES Seating capacity: 4 Wing structure: lower single spar structure Landing gear: front three-point type Brakes: hydraulically driven disc brakes performance Maximum range (km) 1480 Maximum cruising speed (Km/h) 259 Standard cruising speed (Km/h) 239 Maximum structural cruising speed (Km / h) 302 Ultimate speed (Km/h) 370 Maneuver speed (Km / h) 241 Full flap limit speed (Km/h) 193 50% flap speed limit (Km/h) 220 The best glide ratio is 9:1 Maximum range glide speed (Km/h) 183 CAPS start limit speed (Km/h) 246 Landing entrance speed (Km / h) 144 Take-off lift speed (Km/h) 122 Maximum rate of climb speed (Km / h) 178 Maximum angular velocity of climb (Km/h) 154 The stall speed (Km/h) of the smooth form is 128 50% flap stall speed (Km/h) 120 Full flap stall speed (Km/h) 113 Maximum cruising altitude (m) 7680 Take Off Distance (m) 451 Landing distance (m) 700 interior Width (m) 1.5 Height (m) 1.5 Length (m) 3.7 Cabin volume (m³) 3.88 Baggage compartment volume (cubic meters) 0.91 exterior Overall external length (m) 7.9 Overall exterior height (m) 2.7 Wingspan (m) 11.6 weight Maximum take-off weight (kg) 1383 Maximum landing weight (kg) 1383 Maximum weight in the baggage compartment (kg) 59 Maximum zero fuel weight (Kg) 930 Maximum load (Kg) 431 Full fuel load (kg): 282 [1] Turning radius Wingtips (m) 7.41 Front wheels (m) 2.16 Inner wheel (m) 0.15 Outer wheel (m) 2.77 Turning mode Differential brake cornering [2] Aircraft introduction broadcast edit Cirrus was founded in 1984 as a "assembled aircraft" design and production in Barberau, Wisconsin. The first aircraft, the VK-30, gave Cirrus the inspiration to develop a high-performance aircraft. In 1994, Cirrus moved its headquarters to Drews, Minnesota, and began designing and developing the SR20, a four-seat, single-engine, composite aircraft. In 1995, Cirrus signed a contract with EL AL to design and manufacture a concept model of the ST50 turboprop aircraft. A year later, Cirrus produced the fuselage, wings and tail for the U.S. Department of Defense's Tactical Unmanned Aerial Vehicle (TUAV), all of which use composite technology. [3] With its composite construction and advanced aerodynamics, the SR20 aircraft received a type license from the US FAA in 1998. It features a flat instrument panel, a multi-function display, and the ultimate in security innovations, including the ultimate in protection
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