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Mitchell U-2

mitch-supu2

Super U-2

With the Zenoah engine and a considerable evolution in the wing itself Mitchell produced the self-launching U-2 with a fuselage of welded steel tube, and wing of composite structure. The spar is wood, with foam nose ribs and a plywood skin forming a D- tube. Tip rudders provide yaw control. Single-seat single-engined mid-wing mono-plane with conventional three-axis control. Wing has swept back leading and trailing edges, and tapering chord; no tail. Pitch/roll control by stabilators; yaw control by tip rudders; control inputs through stick for pitch/roll and pedals for yaw. Cantilever wing; wing profile modified Worthmann; double -surface. Undercarriage has three wheels in tricycle formation; suspension on main wheels. Push-right go-right nosewheel steering connected to yaw control. Brake on nosewheel. Wood/steel-tube fuselage totally enclosed. Engine mounted above wing driving pusher propeller.

One belongs to the National Soaring Museum.

The Super U-2 is a flying wing with three-axis controls featuring winglet-type hinged rudders for yaw control and stabilators for pitch and roll control. Control surfaces are operated separately, and rudders can be simultaneously deflected. Construction is of chromomoly tubing with Douglas fir and birch plywood. Foam is used for the leading edge ribs and nose cone. Wings are covered with 1 mm birch plywood and ceconite. Tail surfaces and fuselage are covered with ceconite. POWERPLANT: Zenoah G25B-1 in a pusher position above the wing. A 2.25:1 reduction unit turns a two blade wooden propeller made by Woody’s Prop Shop. Fuel is carried in a polypropylene tank installed in the wing. LANDING GEAR: Solid tricycle gear with a steerable nosewheel and a nosewheel friction brake. Main and nose wheels are 10½-inch. OPTIONS: Cuyuna 430R Power Pack, Blueprint plans.

The prototype of the U-2 Super Wing made its first flight in the Spring of 1980 and was presented more as a powered glider with soaring capability than as an ultralight. Initially this flying wing was even envisaged as having a retractable tricycle undercarriage, although this was dropped in favour of having com-pletely faired-in main gear.

With a glide angle of 20/1 at 45 mph (72 kph) the U-2 is perfectly happy with a low-powered engine like the single cylinder McCulloch Mc101 derated to 10hp, however, the aircraft was designed to be powered by engines up to 30 hp and Mitchell Aircraft have offered a kit since 1981 with, as an option, either Zenoah G25B 20hp or Cuyuna 430R 30 hp engines. The design philosophy remains very close to that of the B-10 Mitchell Wing but is applied to a more complex machine, so the amount of time for assembly is considerably more, around 250 h for the major fabrication and 100 h for finishing off. It is classified as an experimental home-built and not an ultralight in the USA, requiring the pilot to have at least a private pilot's licence.

Prototype

Engine: McCulloch 125cc, 10 hp
Gross wt: 450 lbs
Empty wt: 225 lbs
Max pilot wt: 250 lbs
First year built: 1979

U-2
Engine: Zenoah
Wing span: 10.36m / 34ft
Wing area: 12.63sq.m / 136sq.ft
Empty Weight: 109kg / 240lb
Payload: 154kg / 340lb
Gross Weight: 263kg / 580lb
Wing Load: 20.82kg/sq.m / 4.62lb/sq.ft
L/DMax: 20
Aspect ratio: 8
Seats: 1
Airfoil: Wortmann mod.
Structure: wood, steel tube, foam and resin, fabric cover.

Super U-2
Engine: Zenoah G25B, 20 hp at 6300rpm
Propeller diameter and pitch 52 x 27 inch, 1.32x0.69m
Belt reduction, ratio 10/1
Power per unit area 0.14hp/sq.ft, 1.6 hp/sq.m
Fuel capacity 3.0 US gal, 2.5 Imp gal, 11.4 litre
Length overall 9.0ft, 2.74m
Height overall 3.0ft, 0.91m
Wing span 34.0ft, 10.36m
Chord at root 6.2ft, 1.87m
Chord at tip 2.0ft, 0.61m
Dihedral 6 deg
Sweepback 12 deg
Total wing area 136 sq.ft, 12.6 sq.m
Wing aspect ratio 8.5/1
Nosewheel diameter overall 10 inch, 25 cm
Main wheels diameter overall 10 inch, 25 cm
Empty weight 240 lb, 109 kg
Max take-off weight 550 lb, 249 kg
Payload 310 lb, 141 kg
Max wing loading 4.04 lb/sq.ft, 19.7 kg/sq.m
Max power loading 27.5 lb/hp, 12.5 kg/hp
Max cruising speed 60 mph, 97 kph
Stalling speed 26 mph, 42 kph
Max climb rate at sea level 400 ft/min, 2.0 m/s
Take-off distance 200ft, 61m
Landing distance 200ft, 61m
Range at average cruising speed 180 mile, 290 km

Super U-2
Engine: Cuyuna 430R, 30 hp
Belt reduction
Power per unit area 0.22hp/sq.ft, 2.4 hp/sq.m
Fuel capacity 3.0 US gal, 2.5 Imp gal, 11.4 litre
Length overall 9.0ft, 2.74m
Height overall 3.0ft, 0.91m
Wing span 34.0ft, 10.36m
Chord at root 6.2ft, 1.87m
Chord at tip 2.0ft, 0.61m
Dihedral 6 deg
Sweepback 12 deg
Total wing area 136 sq.ft, 12.6 sq.m
Wing aspect ratio 8.5/1
Nosewheel diameter overall 10 inch, 25 cm
Main wheels diameter overall 10 inch, 25 cm
Empty weight 300 lb, 136 kg
Max take-off weight 550 lb, 249 kg
Payload 250 lb, 113 kg
Max wing loading 4.04 lb/sq.ft, 19.7 kg/sq.m
Max power loading 18.3 lb/hp, 8.3 kg/hp
Load factors; +7.8, -7.8 ultimate
Max level speed 100mph, 161kph
Max cruising speed 70 mph, 113 kph
Stalling speed 37 mph, 60 kph
Max climb rate at sea level 750 ft/min, 3.8 m/s
Min sink rate 180ft/min at 45mph, 0.9 m/s at 72 kph
Best glide ratio with power off 23/1 at 49mph, 79kph
Take-off distance 210ft, 64m
Landing distance 250ft, 76m
Service ceiling 12,000ft, 3660 m
Range at average cruising speed 80 mile, 129 km

 

 

 


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