Enigma 26 Wing area: 26.5 sq.m Pilot weight: 50-70 kg No. of cells: 54 Wing span: 12 m Aspect ratio: 5.4 Min sink: 1 m/s Max speed: 49 kph Price (1998) 3800 DM
Enigma 28 Wing area: 28 sq.m Pilot weight: 68-86 kg No. of cells: 56 Wing span: 12.4 m Aspect ratio: 5.5 Min sink: 1 m/s Max speed: 49 kph Price (1998) 3850 DM
Enigma 30 Wing area: 30.5 sq.m Pilot weight: 80-110 kg No. of cells: 58 Wing span: 12.8 m Aspect ratio: 5.5 Min sink: 0.9 m/s Max speed: 49 kph Price (1998) 3900 DM
Circa 1998, a new version of the Chickinox, the Top 2000 has the tailplane supported by a unique design of boom. Rotax engines of 50 to 80 hp are suitable, or Subaru.
Engine: Subaru 1600, 83 hp Wing span: 9.5 m Wing area: 14.9 sq.m MAUW: 450 kg Empty weight: 220 kg Fuel capacity: 38+22 lt Seats: 2 Max speed: 150 kph Cruise speed: 110 kph Minimum speed: 65 kph Climb rate: 4 m/s Fuel consumption: 15 lt/hr
In October 1988 it was reported that the Indian Air Force had placed an order for 25 Chickinox ultralights to be placed at the disposal of selected flying clubs and for pre-selection of future IAF pilots.
The Limousine S-LSA has elements of the MCR-4S and the Twin-R, designed to fit the LSA category. The airframe is based on the MCR-4S. The cabin is finished with the interior developed for the Twin engine “Twin-R”. It includes the new memory foam seats for comfort. The Limousine S-LSA bascally the MCR-4S certified under the S-LSA category. A two seater factory built in compliance with ASTM standards, with options and the interior designed for the Twin-R. It is a MCR-4S factory built and limited to 2 occupants whereas the 4S comes as a kit.
For its launch, the Limousine S-LSA was offered at 127,728 Euros +GST/VAT ex factory until 31 December 2010.
Engine: Rotax 912S, 100 hp Propeller: 2 blade fix pitch Wing span: 8.72 m / 28 ft 5 in Length: 6.72 m / 22 ft 5 in Height: 1.95 m / 6 ft 4 in Wing area: 8,30 m / 87.7 sq ft Aspect ratio: 9,20 Empty Weight fully equiped: 280 Kg / 616 lbs Structural MTOW: 750 Kg / 1650 lbs Useful load at 600Kg: 320 Kg / 704 lbs Fuel tanks: 2 x 100L=200L Total / 52 US Gal Wing loading: 77 kg/m / 18.8 lb/sq ft Speed at 75% Cruise, FL 0: 128 Kts (240 Km/h) Speed at 75% Cruise , FL80: 139 Kts (257 Km/h) Consumption at 75%: 20.7 L/h / 5.5 US Gal Range standard tanks at 75%: 1342 Nm (2486Km) Speed at 65% & FL110: 132 Kts (245 Km/h) Consumption at 65%: 17.9 L/h / 5 US Gal Range standard tanks at 65%: 1477 Nm (2737Km) Take Off distance: 200 m / 656 ft Climb rate, FL 0: 700 ft/min G loading: +3.8 /-1.5 g Glide ratio: 16/1 Cabin Width: 1.17 m / 46 in
The CR120 is a two-seater directly derived from the CR100. The first flights took place in September 1996, with the optimal performance with 200hp. The 120 has a stronger wing and no flaps. The aircraft built starting from the plans will be able to fly under CNRA (Navigability certificate Restricts Plane), and the kit plane will fly under the CNSK (Special Navigability certificate Kit) “category; experimental”, according to the country of registration.
CR 120 Engine: Lycoming, 200 hp Prop; fixed pitch Wing span; 7.77 m Wing area; 9.74 sq.m Length; 6.2 m Fuel capacity; 85 lt Empty weight; 570 kg MTOW; 850 kg Aileron span; 2.70 m Aileron area; 1.63 sq.m Max manœuvre (Va); 260 km/h Never exceed (Vne); 342 km/h Max turbulent air (Vno); 301 km/h Load factor; +8 /-6 g Rate of climb; 10 m/s Roll rate at 260 km/h; 275 deg/s
The CR100 was conceived and optimized for use in flying-clubs The first flight took place in August 1992. The selected motor (180hp and vp prop) is the least expensive, the CR100 can receive various options, including 200hp with a fixed pitch propeller. A CR100 built from plans will be able to fly under the CNRA (Navigability certificate Restricts Plane). Aircraft from a kit will be able to fly under the CNSK (Special Navigability certificate Kit) / ” category; experimental “, according to the country of registration.
CR 100T
The CR100T is a two-seater directly derived from the CR100. The first flights took place in November 2000. With a nose wheel, 180-200 hp, and variable pitch prop, the CR100T was optimized for reliable and intensive school use.
CR 100
CR 100 Wing span; 8.50 m Wing area; 10.60 sq.m Length; 6.8m Fuel capacity; 85 lt Empty weight; 550 kg Empty equipped weight; 850 kg MTOW; 760 kg Aileron span; 2.17 m Aileron surface; 1.21 sq.m Max manouevre (Va): 260 km/h Max speed (Vne): 346 km/h Max turbulent air (Vno); 301 km/h Design load: +8 /-6 g Max flap extension (Vfe): 185 km/h Rate of climb; 8 m/s Roll rate at 260 km/h; 195 deg/s
CR 100T Engine: Lycoming O-360, 200 hp Wing span; 8.50 m Wing area; 10.60 sq.m Length; 6.8 m Fuel capacity; 85 lt Empty weight; 550 kg MTOW; 850 kg Aileron span; 2.17 m Aileron area; 1.21 sq.m Manoeuvring speed (Va); 260 km/h Max speed (Vne); 346 km/h Max turbulence speed (Vno); 301 km/h Load factor; +8 /-6 g Max flap extn (Vfe); 185 km/h Rate of climb; 8 m/s Roll rate to 260 km/h; 195 deg/s
CR 100 Engine: Lycoming IO-360, 180 hp Wing span: 8.5 m Wing area: 10.6 sq.m MAUW: 854 kg Empty weight: 550 kg Fuel capacity: 40 lt Max speed: 316 kph Cruise speed: 273 kph Minimum speed: 96 kph Climb rate: 8 m/s Fuel consumption: 40 lt/hr Seats: 2 Kit price (1998): £42,300
The design of the MCR R180 incorporates a carbon fuselage derived from the MCR 4S (four-seater with more than 130 sold), a Lycoming O-360 of 180 hp, and a canopy offering a visibility on 180°. Options include a roller of tow cable and a ballistic parachute. The MCR R180 is certificated for kits under CNSK 2 category allowing kits.
Engine: Lycoming O-360, 180 hp Propeller: Sensenich or 4-blade Hoffman Max propeller diameter: 1.94m Wing span; 8.72 m Wing area; 8.31 sq.m Length; 9.2 m Cabin width; 1.20 m Fuel capacity; 2 x 65 lt Empty weight initial version; 450 kg Equipped weight; 750 kg MTOW aerotowing; 600 kg Wing loading aerotowing; 72 kg/sq.m Stall @ MAUW; 83 km/h Stall 600 kg; 74 km/h Manoeuvring speed (Va); 219 km/h Never exceed (Vne); 270 km/h Turbulent air max (Vno); 243 km/h Load factors; +3.8/-1.5 g Flap extension (Vfe); 160 km/h Best towing speed; 90 – 150 km/h ROC w/tow 350 kg: 7.27 m/s ROC w/tow 550 kg: 5.73 m/s ROC w/tow 750 kg: 4.67 m/s
The initial studies of the four-seat MCR-4S started in early 1994, during development of the MCR VLA. The VLA appears first in 1996 and permited the development of the general technology. The airframe, and the high lift devices, such as the double slotted flaps were initially designed to equipped the MCR UL, meanwhile, the control system was directly from the MCR CLUB technology of 1998. The MCR 4-S concept was to fly with four people onboard, cruising at more than 250 km/h, and burning only 20 lt/hr with a 100 hp engine. The research gave wing-tips optimized in a wind-tunnel, and double slotted flaps, providing the MCR 4-S with STOL performances. Designed around a roomy cockpit ; 1,20m width at the rear seats, to allow four people up to 1,95m tall to be easily seated in the airplane, the aircraft is equipped with a very strong oil-pneumatic undercarriage, allowing landings on any type of runways. The 4-S maiden flight was in June 2000. The MCR 4-S has a very light empty weight. The aircraft can carry up to 150% of its own empty weight. Engine options include the 100 hp Rotax 912S, 100 hp turbo charged Rotax 914, and 120 hp Jabiru 3300. The MCR-4S can be fitted with other options such as Ballistic Recovery System parachute, extended range fuel tanks, and toe operated hydraulic brakes. The MCR-4S is available in kit form in respect with the CNSK regulation (specific kit airworthiness certificate) or in the “experimental” category depending on the registration country.
The MCR PickUp is a two seater version of the MCR 4S with a large trunk instead of the rear seats.
Wing span; 8.72 m Wing aera; 8.30 sq.m Aspect ratio; 9.20 Cabin Width; 1.20 m Fuel capacity standard; 2 x 65 lt Extended range fuel tanks; 2 x 100 lt Empty weight Basic version; 300 kg Equipped empty weight; 350 kg Max. Takeoff weight; 750kg Wing loading; 90 kg/sq.m VSO (stall speed landing configuration); 83 km/h Va (Maneuvering speed); 219 km/h Vne ( Never exceeding speed); 270 km/h Design maneuvering speed; 300 km/h Vno (Normal Operation Speed); 243 km/h G loading; +3.8 /-1.5 g Vfe (Flaps extended speed); 160 km/h
Engine; Rotax 912, 95-100 hp Cruising 75%, FL 0; 245 km/h Cruising 75%, FL 80; 236 km/h Fuel consumption 75%; 20.7 lt/hr Range ,std Tanks 75%; 1079 km Cruising 65% FL110; 255 km/h Fuel consumption 65%; 17.9 lt/hr Range ,std Tanks 65%; 1846 km Takeoff roll; CS. Prop; 350 m Climb rate FL 0, CS. Prop; 750 fpm
Engine; Rotax 914, 100-115 hp Cruising 75%, FL 0; 245 km/h Cruising 75%, FL 80; 272 km/h Fuel consumption 75%; 20.7 lt/hr Range ,std Tanks 75%; 1079 km Cruising 65% FL110; 255 km/h Fuel consumption 65%; 17.9 lt/hr Range ,std Tanks 65%; 1846 km Takeoff roll; CS. Prop; 350 m Climb rate FL 0, CS. Prop; 900 fpm
DynAero MCR Pick-up Stall: 34 kt / 39 mph / 63 kmh Cruise: 135 kt / 155 mph / 250 kmh VNE: 146 kt / 168 mph / 270 kmh Empty Weight: 260 kg / 573 lbs MTOW Weight: 600 kg / 1323 lbs Climb Ratio: 1250 ft/min / 6 m/s Take-off distance (50ft obstacle): 240 ft / 73 m Landing distance (50ft obstacle): 350 ft / 107 m
