Form I L Paraglider circa 1998. Wing area: 27.5 sq.m Certification: Afnor Pilot weight: 60-90 kg No. of cells: 56 Wing span: 12.2 m Aspect ratio: 5.4 Min sink: 1 m/s Max speed: 49 kph Price (1998) 4750 SF
Form I M Paraglider circa 1998. Wing area: 25.3 sq.m Certification: Afnor Pilot weight: 45-70 kg No. of cells: 56 Wing span: 11.7 m Aspect ratio: 5.4 Min sink: 1 m/s Max speed: 50 kph Price (1998) 4650 SF
Form I XL Paraglider circa 1998. Wing area: 30 sq.m Certification: Afnor Pilot weight: 85-115 kg No. of cells: 56 Wing span: 12.7 m Aspect ratio: 5.4 Min sink: 1 m/s Max speed: 49 kph Price (1998) 4850 SF
China has not officially confirmed the first flight of the KJ-3000 aircraft, which will significantly enhance its early warning capabilities. The KJ-3000 is based on the People’s Liberation Army Air Force (PLAAF) Y-20 transport aircraft and is the latest addition to China’s “eye in the sky” arsenal of early warning aircraft.
The rotodome is a discus-shaped rotating radome that allows the detection and tracking of targets by providing 360-degree coverage. Some experts speculate that the bulge on the tail may be related to the integration of some advanced communication systems.
The aircraft is powered by the domestically-produced WS-20 high-bypass turbofan engine, like the Y-20B transport aircraft that it is based on. It is anticipated to generate approximately 31,000 pounds of thrust. As per some unconfirmed claims, the aircraft would have a detection range exceeding 360-500 km.
The KJ-3000 can carry more payload—up to 66 tons— 16 tons more than the KJ-2000. Moreover, the WS-20 engines provide more thrust and fuel efficiency, enabling longer flight operations.
The aircraft could operate as a complete command center since it integrates C4ISR (Command, Control, Communications, Computers, Intelligence, Surveillance, and Reconnaissance) technologies, allowing for better coordination between the land, sea, and air domains.
Two major Chinese aviation companies, Shaanxi Aircraft Corporation and Xi’an Aircraft Corporation, expressed interest to develop the Y-20 aircraft, but Xi’an was announced as the manufacturer of Y-20 in 2007.
Developed by Xi’an Aircraft Industrial Corporation and was officially launched in 2006 the Xi’an Y-20 (Chinese: 运-20; pinyin: Yùn-20; literally: “transport-20”) is a large military transport aircraft. The official codename of the aircraft is Kunpeng (Chinese: 鲲鹏), after the mythical bird that can fly for thousands of miles described in the ancient Chinese Taoist classic Zhuangzi. However, within the Chinese aviation industry itself, the aircraft is more commonly known by its nickname Chubby Girl (Chinese: 胖妞), because its wide fuselage in comparison to other Chinese aircraft previously developed in China.
The aircraft was primarily designed and developed in China by Xi’an Aircraft Industrial Corporation under Tang Changhong. Certain parts of the wing such as the triple-slotted trailing-edge flaps were developed by the Ukrainian Antonov Design Bureau. The Y-20 uses components made of composite materials. The composites are produced in China, whereas in the past they had to be imported. The Y-20’s cabin incorporates flame-retardant composites developed by the 703 Institute of the China Aerospace Science and Technology Corporation (CASC). The 703 Institute was created in March 2009 with development taking three years. The performance of the composites is reportedly comparable to those that fulfill FAR Part 25.835. The 703 Institute achieved another milestone by establishing a comprehensive Chinese evaluation and certification system for aircraft composite materials based on international standards.
The Y-20 is the first cargo aircraft to use 3D printing technology to speed up its development and to lower its manufacturing cost. Model-based definition (MBD) is also used, and it’s the third aircraft to utilize MBD technology in the world, after Airbus A380 (2000) and Boeing 787 (2005). A project team to implement MBD for Y-20 program was formally formed in October 2009, and after the initial success in application on the main landing gear, MBD application was expanded to the entire aircraft and became mandatory for all contractors and sub contractors of the Y-20 program. The implementation of MBD was initially met with strong resistance, with only a third of suppliers agreeing to implement MBD. However, the general designer of Y-20 declared that those who refused to implement MBD will be banned from participating in the Y-20 program, thus forcing everyone to comply, resulting in increases in productivity. The implementation of MBD greatly shortened the time required, for example, without MBD, installation of wings takes a month or two, but with MBD adopted, the time is drastically shortened to just a few hours, and in general, the design work reduced by 40%, preparation for production reduced by 75%, and manufacturing cycle reduced by 30%. In addition to 3D printing, Y-20 is also the first aircraft in China adopting associative design technology (ADT) in its development. Headed by the deputy general designer of structural design, Mr. Feng Jun (冯军), the initial attempt to implement ADT actually failed after two months spent on application on the nose section. It was only after the second attempt that took another three months on the application on wings did ADT became successful. The adaptation of ADT greatly shortened the development time by at least eight months, and modification of wing design that previously took a week is shortened to half a day.
The Y-20 airlifter has a glass cockpit, which accommodates three crew members. Cargo is loaded through a large aft ramp that accommodates rolling stock. The Y-20 incorporates a shoulder wing, T-tail, rear cargo-loading assembly and heavy-duty retractable landing gear, consists of three rows, with a pair of wheels for each row, totalling six wheels for each side. The structural test was completed in 194 days as opposed to the 300 days originally planned, thanks to the successful development and application of an automated structural strength analysis system. According to the deputy general designer, the shortest take-off distance of Y-20 is 600 to 700 meters. Y-20 incorporates a total of four LCD EFIS, and the development of EFIS for Y-20 utilizes virtual reality via helmet mounted display. Eight types of different relays used on Y-20 are developed by Guilin Aerospace Co., Ltd. a wholly own subsidiary of China Tri-River Aerospace Group Co., Ltd.(中国三江航天集团), which is also known as the 9th Academy of China Aerospace Science and Industry Corporation (CASIC).
It was reported that the Y-20 started ground testing from December 2012, including runway taxi tests. The aircraft made its maiden flight lasting one hour on January 26, 2013 at Shaanxi Yanliang Aviation Base. During landing in first flight, it was reported that the Y-20 prototype bounced once before finally settling on runway due to high landing speed. In December 2013, a new Y-20 prototype took to the sky.
The Y-20 is powered by four 12-ton thrust Soloviev D-30KP-2 engines, and all early production units are likely to be similarly powered. The Chinese intend to replace the D-30 with the 14-ton thrust WS-20, which is required for the Y-20 to achieve its maximum cargo capacity of 66 tons. The Shenyang WS-20 is derived from the core of the Shenyang WS-10A, an indigenous Chinese turbofan engine for fighter aircraft.
In 2013, Shenyang Engine Design and Research Institute was reportedly developing the SF-A, a 28700-pound thrust engine, for the Y-20 and the Comac C919. The SF-A is derived from the core of the WS-15. Compared to the WS-20, the SF-A is a conservative design that does not seek to match the technology of more modern engines.
In late 2017, it is revealed that domestic Chinese turbofan WS-18 has begun flight test on Y-20. Compared with Russian Soloviev D-30, WS-18 is 300 kg lighter, weighing at 2000 kg; with thrust increased from 12.5 ton of D-30 to 13.2 ton; and fuel consumption of WS-18 is also reduced in comparison to D-30, and the mean time between overhaul of WS-18 is 3000 hours. However, because the increase in thrust is not significant in comparison to D-30, WS-18 is like to be a stopgap measure before WS-20 is ready. The production aircraft are equipped with WS-20 engines.
The aircraft is equipped with a retractable landing gear comprising two main landing gear units and a nose unit. Each of the two main units on either side of under-fuselage features six wheels, which are arranged in a two-two-two layout from front-to back. The steerable nose gear includes a standard twin-wheel leg unit. The landing gear allows take-offs and landings on rough airfields or unpaved runways.
In 2014 the PLA National Defence University’s Center for Economic Research recommended the purchase of up to 400 Y-20s, comparing the PLAAF’s needs with the existing airlifter fleets of the United States and Russia. In June 2016 Jane’s reported that up to 1,000 Y-20s are being requested by the Chinese military.
On 6 February 2016 the Y-20 was flown for the first time and pictures of the fifth prototype (serial number 788) in flight appeared on Chinese military webpages. Other known prototypes carry identification numbers 781, 783 and 785. On 27 January 2016, former Chinese test pilot Xu Yongling had reported in a Xinhua article that Chinese aviation industry officials had stated that the Y-20 “completed development” at the end of 2015. In June 2016, the first two Xian Y-20 aircraft were delivered to the People’s Liberation Army Air Force (PLAAF).
On 6 July 2016 the first serial Y-20 (serial number 11051) was handed over to the PLAAF in a ceremony. The second aircraft serialed 11052 followed soon after – it is assigned to the 12th Regiment of the 4th Transport Division at Qionglai, Chengdu. On 8 May 2018, it was announced by PLAAF’s spokeperson Shen Jinke that Y-20 had “recently conducted its first joint airdrop training with the country’s airborne troops”.
At least two aircraft stationed at Qionglai Air Base since July 2016. Commercial satellite imagery captured on 9 December 2017 suggests that at least three more Xian Aircraft Corporation Y-20 Kunpeng transport aircraft have entered service with China’s People’s Liberation Army Air Force (PLAAF). In these images there are a total of 5 Xi’an Y-20’s lined up at Qionglai Airbase near Chengdu in China’s southwestern Sichuan Province.
The YY-20A tanker, bearing the serial number 20646, was spotted in February 2025.
YY-20A
Derived from the Xi’an Y-20 strategic transport, the YY-20A tanker variant can haul up to 90 tons of fuel, tripling the capacity of the aging H-6U tankers it’s replacing.
2023 analysis pointed to the YY-20B’s “hot and high” takeoff capability—enabled by the WS-20 engines—as a game-changer, allowing operations from rugged, high-altitude bases that could support a Taiwan contingency.
The base Y-20A transport, powered initially by Russian D-30KP-2 engines, boasts a 66-ton payload and a range of up to 7,800 kilometers when fully loaded, capable of carrying everything from ZTZ-99 tanks to medical supplies.
The YY-20A tanker variant, introduced in 2022, swaps cargo for fuel pallets, featuring two underwing refueling pods and a centerline drogue for large aircraft like the H-6N bomber or KJ-500A AEW&C platform, monitored by IIR/TV cameras for precision.
The Y-20B, rolled out by 2023, upgrades to four Shenyang WS-20 high-bypass turbofans, boosting thrust to 31,000 pounds per engine and enhancing the range and short-field performance. A YY-20B tanker sub-variant, spotted in late 2023, likely builds on this, though some speculate the Y-20B’s modular design allows any unit to double as a tanker with minimal reconfiguration.
Advanced avionics, a glass cockpit with heads-up displays, and composite materials round out a platform that’s as modern as it is massive, with a 50-meter wingspan and 47-meter length.
Analysts see a niche for the Y-20E export variant, powered by WS-20s.
In 2025 production capacity was ramping up and a civilian Y-20F-100 variant pitched for commercial use.
Specifications (estimated) Engines: 4 × Soloviev D-30KP-2 turbofans Wingspan: 45 m (147 ft ~ 164 ft) Wing area: 330 m² (3550 ft²) Length: 47 m (154.2 ft) Height: 15 m (49.2 ft) Empty weight: 100,000 kg (220,400 lb) Max takeoff weight: 220,000 kg (485,000 lb) Payload: 66 tonnes (145,505 lb) Max wing loading: 710 kg/m² (145 lb/ft²) Cruise speed: Mach 0.75 Range max payload: 4,500 km Range 40 ton payload: 7,800 km Service ceiling: 13,000 m (42,700 ft) Crew: 3: pilot, copilot & load master
This major aircraft company was established in 1958. In 1961 it took over from Harbin production of the H-6, a Chinese version of the Soviet Tupolev Tu-16 Badger bomber, and also developed the H-6D as a cruise missile carrier. Produced the Y7 short/medium-range transport based on the Soviet An-24, the first flying in December 1970, and improved versions continue in production. Y7H and Y7H-500 are military and civil versions of the An-26. A supersonic strike aircraft first flew in 1989 as the JH-7, which might have entered service in small numbers with the PLA Naval Aviation for maritime strike duties from 1994. An export version of JH-7 was revealed in November 1998 as the FBC-1 Flying Leopard.
Xenon was designed by French aircraft designer Raphael Celier and was manufactured in Poland to the French Ultralight category standards.
Celier Aviation established its reputation with the two-seat side-by-side configuration Celier Xenon 2 series of autogyros. By 2011 over 100 of these were flying.
A Celier Xenon 2 on display at Sun ‘n Fun in Lakeland, Florida, United States, 2008.
This high performance ultralight autogyro was available as a kit or ready to fly. Registered as an LSA. Delivered fully factory built starting at $61,000 in 2009. The composite structure is the airframe, providing lightness and incorporating a full roll cage to protect the occupants. The cabin is 10″ wider than a Cessna 172 and the two pilots are separated by a 10″ console and arm rest. Behind the seats is a very large luggage compartment. The Aircopter rotor blades are aluminum yet use titanium for strength and tip weighting for higher inertia. The DUC R propeller features a spoon blade with a wider tip and built in feathering. It is carbon forged under high pressure and a carbon fiber spinner is fitted. The box tail section is directly in the propeller slipstream and is on a long lever arm for effectiveness with or without engine power. The 28″ high cabin is soundproofed, with interior carpeting and heated leather bucket seats, and the Xenon meets European noise standards. The Xenon is available with a choice of 3 different engines. The standard model comes with a Rotax 912S Engine that delivers 100 horsepower. The 914 Model features a Rotax turbo that delivers 115 horsepower for up to 5 minutes after which the engine delivers a continuous 100 horsepower. The high altitude or extra climb ability model is the 912 RST version which has a Rotax 912 sporting a custom designed Mitsubishi turbo delivering 122 horsepower for take-off followed by a continuous 110 horsepower with full time turbo boost. The doors are removable for flight, leaving a full wrap around optical windshield with overhead windows and foot well windows, allowing near unobstructed viewing. The instrument panel is shock mounted to be vibration free and includes full instrumentation for flight performance and engine monitoring. Flight instruments include: altimeter, airspeed indicator and vertical speed indicator. Rotor tach and fuel are separate gauges while graphic digital engine monitor uses colored LEDs to keep track of engine tach, CHT and EGT gauges, volt/amp meter, oil pressure and temperature, fuel flow, turbine temperature and manifold pressure. There is a 12 volt power plug for the portable GPS or MP3 player. Options include intercoms, VHF radio and transponder with altitude encoder. The console arm rest puts the throttle and 280 rpm pre-rotator under one hand. Circuit breakers control the panel and landing lights and overhead heat vents are fitted. Options vary depending on the model but your Xenon is available with propeller spinner, special metallic paint, cabin and blade covers, larger rotors, removable joystick, adjustable pedals, heated leather seats or a ballistic parachute.
Engine: Rotax 912S, 100 hp Propeller: 3 Blade DUC Windspoon 68.5 in Max TO weight: 1,155 lbs. Empty Weight: 583 lbs Payload: 462 lbs Rotor blades: Type 8H12 Aircopter Extruded Aluminum Rotor Diameter: 27.55 ft Dics Area: 596.1 sq. ft Total Width: 86.6 in Total Length: 192.9 in Total Height: 110.23 in Cabin Width: 49.2 in Pre-rotator: Mechanical 280 RRPM Wheel Diameter: 400×4 Vne: 108 kt / 124 mph / 200 kph Minimum Speed: 19 mph Cruise 75%: 75 mph Max speed: 105 mph Climb Rate: 600-1200 fpm Glide Ratio: 3:1 Service Ceiling: 15,000 ft Endurance: 4 hr + res Take off Dist: 100-300 ft Landing Dist: 15 ft Fuel Capacity: 22 USG Fuel Burn @ 65% pwr: 4.8 USGPH Endurance: 4 hrs + res
Engine: Rotax 914, 115 hp Empty Weight: 616 lbs Propeller: 3 Blade DUC Windspoon 68.5 in Max TO weight: 1,155 lbs. Rotor blades: Type 8H12 Aircopter Extruded Aluminum Payload: 484 lbs Rotor Diameter: 27.55 ft Dics Area: 596.1 sq. ft Total Width: 86.6 in Total Length: 192.9 in Total Height: 110.23 in Cabin Width: 49.2 in Pre-rotator: Mechanical 280 Wheel Diameter: 400×4 Vne: 108 kt / 124 mph / 200 kph Minimum Speed: 19 mph Cruise 75%: 87 mph Max speed: 115 mph Climb Rate: 600-1200 fpm Glide Ratio: 3:1 Service Ceiling: 15,000 ft Endurance: 4 hr + res Take off Dist: 100-300 ft Landing Dist: 15 ft Fuel Capacity: 22 USG Fuel Burn @ 65% pwr: 4.8 USGPH Endurance: 4 hrs + res
Engine: Rotax 912 RST, 122 hp Empty Weight: 605 lbs Propeller: 3 Blade DUC Windspoon 68.5 in Max TO weight: 1,155 lbs. Rotor blades: Type 8H12 Aircopter Extruded Aluminum Payload: 550 lbs Rotor Diameter: 27.55 ft Dics Area: 596.1 sq. ft Total Width: 86.6 in Total Length: 192.9 in Total Height: 110.23 in Cabin Width: 49.2 in Pre-rotator: Mechanical 280 RRPM Wheel Diameter: 400×4 Vne: 108 kt / 124 mph / 200 kph Minimum Speed: 19 mph Cruise 75%: 99 mph Max speed: 121 mph Climb Rate: 600-1200 fpm Glide Ratio: 3:1 Service Ceiling: 15,000 ft Endurance: 4 hr + res Take off Dist: 100-300 ft Landing Dist: 15 ft Fuel Capacity: 22 USG Fuel Burn @ 65% pwr: 4.8 USGPH Endurance: 4 hrs + res
Xenon Gyrocopter Engine: Rotax 912RST (turbo) Height: 2.8m Fuselage width: 2.2m Length: L4.9m Empty weight: 294kg Max take off weight: 544kgs Payload: 240kgs Fuel capacity: 87 litres VNE: 113 knots Cruise speed: 86 knots Min speed: 16 knots Rate of climb: 800-1200 fpm Take off Distance: 35-100 meters Landing distance: 0-5 metres Range: 4hours plus Seats: 2
A rocket powered version of the Long-Ez flew twice at Mojave in 2002. Its twin rocket motors of 400 lb thrust each burned for less than three minutes after which it took seven minutes to glide to landing. It is fuelled by isopropyl alcohol and liquid oxygen. The engines can be shut-down and restarted in flight.
Jerzy Krawczyk, in addition to Ekolot’s Junior and Topaz, has several light aircraft, crop sprayer, and sailplane designs to his credit. In creating the self launching Elf sailplane, he employed composite sandwich and carbon structures to achieve the exceptional strength and durability required to pass UK BCAR Section ‘S’ airworthiness certification.
The Elf prototype used the JPX 330 engine which, unfortunately, was withdrawn from production in 2006 after over 20 years in the market. Fortunately, Compact Radial Engines in Canada has produced a very similar unit. This is 20% more powerful than the JPX and also employs a clutch which eliminates folding prop ‘chatter’ on start-up and allows the prop to fold whilst the engine is on idle. This engine has displayed instant re-start capability.
The Elf employs full span flapperons, and airbrakes, and has excellent rudder/stick co-ordination. The NN17-18 aerofoil possesses mild stall characteristics and overall, the handling conveys a strong sense of stability and security to the pilot.
Production aircraft will have the more powerful Compact Radial engine and a 126cms prop with a projected climb rate of 500 ft/min.
KR-010 “Elf” G-CIUO over Scotland
Engine off, the Elf with it’s 120 ft/min sink rate is capable of slowing down to exploit the slightest lift and core the smallest thermal. This is where the fun and skill challenge begins and where, if the pilot falls out of lift into sink, he can be confident of a quick engine restart and climb back to the area of lift.
Prototype Engine: JPX 330, 24 hp Prop dia: 116cms , folding Weight: 145 kg (with BRS) Gross Weight: 260 kg Area: 10.8 sq/m Span: 11.2 m Length: 5.7m Aerofoil: NN18-17 Fuel Capacity: 15 litres (3 hours + reserve) Proof Load: +6 / -3 Max Pilot Height: 1.9m (6’3”) Max Pilot Weight: 100kg (220lbs) Cruise: 50 mph at 5,100rpm Max Climb: 400ft/min at 30mph Stall: 27mph Best L/D: 26.4:1, 150ft/min at 45mph Min Sink: 120ft/min at 39 mph Airbrake: 300ft/min at 45mph (13:1) Fuel burn: 4.5 litres/hour
Joel Koechlin of Raj Hamsa the manufacturing company in India, wanted to build a new aircraft, which kept the features of the original Xair, and add all the things owners wanted. Like bigger doors, adjustable seats, folding wings, more speed, overhead visibility, better comfort etc. The Hanuman is very different from the existing X-Air’s. The Hanuman has been designed to accept a larger range of engines which include the Jabiru 2.2, the Rotax 912 / 914 and some of the bigger Hirth 4 cylinder engines, the aircraft would also perform reasonable well on the 582 or 618 Rotax two strokes.
The flap lever has been sited on the top left hand side of the cabin, so no more need to change hands on the stick. The seat belts now come through the headrest which means they fit better over the shoulders. The seats are adjustable. The X-Air also has a solid wooden floor in the cockpit.
The Standard Xair pilots had a draft that came between the seats, but now there is a piece of clear fabric sewn in place to seal it up, but still allowing you to see the big 80 litre fuel tank.
A Baggage compartment is located behind the seats and the dashboard has now also been sloped forward & closer to the occupants. A purpose surround for the compass is now incorporated on the top of the dashboard.
The Hawk like the original X-air is fitted with full Dual controls, i.e. two sticks, two throttles and the pilot has toe operated brakes; aircraft used for training can also be fitted with an emergency brake operated by the instructor. All the controls are now under the floor so there is a much better & cleaner look.
The Doors are now wide so access is easy. They hinge at the front so they are totally out of the way when opened and allow excellent access. Overhead visibility is provided with four clear lexan panels in the fiberglass roof section.
The Hanuman model is generally fitted with the Rotax or Jabiru 80 hp four stroke engines and these generally have a different instrument specification to the standard two stroke powered X-Air aircraft. The Jabiru 2.2 and Rotax 912 engines both need to modify the engine mounts.
The Hawk has achieved BCAR ‘S’ Certification and can be built from a kit, through the PFA system. This aircraft is a 2 place aircraft, and features the Jabiru engine, a wing fold system, Kevlar reinforced, coated fabric, a ‘proper’ bungee-sprung, undercarriage; dual controls and a wide, comfortable cockpit with excellent forward/side visibility. A cockpit heat system is also included.
The X-Air can be pulled down in about 15 minutes. Firstly, the Velcro attached wing nappy is removed, the wing skin tensioning belts are released, the aileron cable is detached and with the assistance of a helper the wing struts are removed and finally, the wings are detached from the main fuse tube. All the wing removal can be done without tools. The wing can be reattached in about 25 minutes.
The suspension design is similar to shock absorbers on a motorcycle and can handle all the bumps and potholes on grass and bush strips with ease. The front wheel has dual shock suspension with trailing link design steering; the trailing link design straightens up immediately on touch down, so even landing in cross wind is relatively easy in the X-Air. The shock absorber design used on the X-Air offers rebound dampening. The undercarriage is rated to 9 g’s.
A Clear illustrated build manual with colour photographs and pre assembled parts make assembly easy. Some of the added benefits are: Cabin Heat Easy Remove/Folding Wings Four Stroke Engine 90+ mph Cruise 60 litre fuel tank now up to 5+hrs flying time Quick Adjusting seats on Sliding Rails 85hp Jabiru 2200 Engine as standard
The X-air Hawk is the UK/Eire Version of the Xair-H, also referred to as the Hanuman in other countries.
The Xair Hawk is available both as a BCAR Section ‘S’ Microlight and as a Group A VLA at 499kg.
The aircraft has been in the design for some years, undergoing various tests and trials, with the first showing of the prototype at Blois in 2002.
X-Air Hawk Engine:85hp Jabiru Prop: 2 blade wooden Newton Length 6.09m/20ft Wing span 10.05m/33ft Max height 2.4m/7ft 10ins Wheel track 1.74m/68 ins Wing area 13.92sqm Wheel size 500 mm/16 ins Wheel base 1.50m/59 ins Empty weight Jabiru 266kg/588 lb Stall speed: 33 mph Vne: 125 mph Cruise Speed: 90 mph Climb Speed: 55 mph Rate of Climb: 900 ft/min Glide Ratio: 7@40 mph Fuel Consumption: 10 Ltr/hr Two seater, side by side 3 Axis; Ailerons, elevator and rudder Full dual control – two sticks, two throttles High wing, conventional front mounted engine Tricycle Gear, with Elastic shock absorbtion Steerable nose wheel, linked to rudder pedals Toe operated differential brakes Enclosed cockpit, lexan windscreen Elevator trim 3 stage Flaps 80L Fuel Tank Polyester Sail Cloth G loading +6 -3 6061 T6 Aluminium Tubing epoxy/polyurethane painted
Hanuman Stall: 29 kt / 33 mph / 53 kmh Cruise: 76 kt / 87 mph / 140 kmh VNE: 105 kt / 121 mph / 195 kmh Empty Weight: 263 kg / 580 lbs MTOW Weight: 450 kg / 992 lbs Climb Ratio: 900 ft/min / 4.8 m/s Take-off distance (50ft obstacle): 360 ft / 110 m Landing distance (50ft obstacle): 720 ft / 220 m