The Monex made its maiden flight on September 30, 1980. It is a high-performance, single-place, conventionally geared aircraft, and was used primarily as a research and development airplane for the Moni. The construction technique used in Monex is reflected in the Moni series of aircraft available in kit form.
Engine Monnett “Aero Vee” VW 2180 cc
Gross Wt. 650 lb
Empty Wt. 380 lb
Wingspan 16’8”
Length 15’2”
Fuel capacity 10 USG
Top speed 230 mph
After enjoying success with his original VW-powered Sonerai, John Monnett decided to develop the Sonerai II, a tandem-seated version. Both pilot and passenger sit under a bubble canopy which is hinged on the right side. The Sonerai II differs mainly by being slightly larger, making use of a more powerful engine, and by being stressed for aerobatics when flown by the pilot alone.
The II-L is the same aircraft but with a “low-wing”. The low-wing version is especially popular with 6 foot plus pilots, as the pilot legs go over the main spar carry through structure.
The Sonari II was also available as a low-wing nose gear two place, or the Sonerai II-Stretch: A low-wing model 18″ longer than the original, as a low-wing taildragger and a low-wing tri-gear. The Sonerai II-LT is the steerable nose wheel version.
The Sonerai II series will accept VW power plants from 1700cc – 2276cc.
Price in 1982: $2,742 (Excludes engine).
Monnet Sonerai II November 1983 article
All models of the Sonerai II use a minimum of different sizes of materials to reduce the cost, without hampering the integrity of the design. The wing is all aluminum and is composed of two panels that easily fold along side the fuselage enabling the Sonerai II, II-L and II-LT to be towed tail first on its own gear. Stainless steel cherry rivets are used to skin the wing. The fuselage and tail surfaces are constructed of standard sizes of 4130 steel tubing that are fabric covered. All aluminum sheet used is 2024-T3 .025″ except for the spars which are .040″.
The fiberglass cowling removes easily to allow complete access to the engine, magneto, tank and instruments. The landing gear is a formed aluminum spring with 5″ wheels and 3/4″ axles. A tapered tailspring rod is used for the tailwheel (II and II-L) All Sonerai II’s feature a l0 US gallon main tank with the option of a 6 gallon auxiliary tank carried on the passengers floor board (without passenger).
Sonerari II
Engine: VW 1700 – 2180cc, 65-70-hp
Span: 18′ 8″
Length: 18′ 10″
Height: 5′ 5″
Wing area: 84 sq.ft
Empty weight (no starter): 236 kg /520 lb
Useful load: 430 lb
MTOW Weight: 431 kg / 950 lbs
Wing loading at gross: 11.3 lb/sq.ft
Fuel capacity – std: 10 USG
Fuel capacity – opt: 6 USG
Seats: 2 tandem
Design limit at full gross: +/- 4 G
Aerobatic limit solo w/755 lb: +/- 6 G
Take off distance: 900 ft
Stall speed: 39 kt / 45 mph / 72 kmh
Landing speed: 58 mph
Maneuvering speed: 115 mph
Cruising spped at 75%: 122 kt / 140 mph / 225 kmh
Vne: 174 kt / 200 mph / 322 kmh
Range w/45 minute reserve: 245 sm
Rate of climb at gross: 500 fpm / 3 m/s
Takeoff run 900 ft
Take-off distance (50ft obstacle): 900 ft / 274 m
Landing roll 500 ft
Service ceiling: 14,000 ft
Seats: 2
Sonerai II-L
Engine: VW 2180cc, 70 hp
Max wt: 925 lbs
Empty wt: 510 lbs
Fuel capaci¬ty 10 USG
Height: 5.5 ft
Wingspan 18.8 ft
Length 18.7 ft
Climb rate: 500 fpm
Top speed: 175 mph
Cruise: 140 mph
Stall 45 mph
Range: 245 sm
Takeoff run: 900 ft
Landing roll: 900 ft
Service ceiling: 14,000 ft
Seats: 2
Wing area: 84 sq.ft
Tail wheel
Sonerai II-LS
Engine: VW 2180cc, 70 hp
Max wt: 1150 lbs
Empty wt: 540 lbs
Fuel capaci¬ty 10 USG
Height: 5.5 ft
Wingspan 20.4 ft
Length 18.7 ft
Wing area: 84 sq.ft
Climb rate: 700 fpm
Top speed 170 mph
Cruise 140 mph
Stall 50 mph
Range: 600 sm
Takeoff run: 700 ft
Landing roll: 900 ft
Service ceiling: 14,000 ft
Seats: 2
Tail wheel
Sonerai II-LT
Engine: VW 2180cc, 70 hp
Max wt: 1150 lbs
Empty wt: 540 lbs
Fuel capaci¬ty 10 USG
Height: 5.5 ft
Wingspan 18.8 ft
Length 20.4ft
Climb rate: 700 fpm
Top speed: 170 mph
Cruise 140 mph
Stall 50 mph
Range: 245 sm
Takeoff run: 700 ft
Landing roll: 900 ft
Service ceiling: 14,000 ft
Seats: 2
Wing area: 84 sq.ft
Nose wheel
Sonerai II-LTS
Engine: VW 2180cc, 70 hp
Max wt: 1150 lbs.
Empty wt: 540 lbs
Fuel capaci¬ty 10 USG
Height: 5.5 ft
Wingspan 20.4 ft
Length 18.7 ft
Wing area: 84 sq.ft
Climb rate: 700 fpm
Top speed 170 mph
Cruise 140 mph
Stall 50 mph
Range: 600 sm
Takeoff run: 700 ft
Landing roll: 900 ft
Service ceiling: 14,000 ft
Seats: 2
Nose wheel
Great Plains Soneri II
Empty weight: 227 kg
Wing span: 5.7 m
Wing area: 7.73 sq.m
Fuel capacity: 38 lt
Engine: VW 2100, 70 hp
MAUW: 522 kg
Seats: 2
Max speed: 282 kph
Cruise speed: 225 kph
Minimum speed: 80 kph
Climb rate: 3 m/s
Fuel consumption: 12 lt/hr
Plan price (1998): US$99.95
Kit price (1998): US$5500
The Sonerai I is a mid-wing sport plane, racer, designed and first built in 1971to meet all Professional Race Pilots Association (PRPA) and Formula Vee Racing requirements for 1600cc Volkswagen powered aircraft. Its wings are 2024-T3 aluminum.025″ except for the spars which are .040″. The wing is composed of two panels that fold along side the fuselage, enabling the Sonerai I to be towed tail first on it’s own gear. Stainless steel cherry rivets are used to skin the wing. The fuselage and tail are of standard 4130 chrome moly tubing.
The Sonerai I uses a minimum of different sizes of tubing to reduce the cost. Cowling is fiberglass, and fuselage and tail surfaces are fabric covered. The fiberglass cowling removes easily to allow complete access to the engine, magneto, tank and instruments. The landing gear is manufactured from 1/2″ x 5″ 2024T-351 aluminum. The Sonerai I will accept engine displacements from 1600cc through 2180cc.
Price in 1982: $2,527.
The Sonerai was also marketed as the Great Plains Aircraft Sonerai (1998). The Sonerai I can handle +/- 6 G’s with the “S” wing and will do 170 mph flat out with a Great Plains 2180cc engine.
Engine: VW 1600 – 2180cc
Span: 16 ‘ 8″
Length: 16′ 8″
Height: 5 ‘
Wing area: 75 sq.ft
Empty weight: 200 kg / 440 lb
Useful load: 260 lb
Gross weight: 318 kg / 700 lb
Fuel capacity – std: 11 USG
Design limit at full gross: +/- 6 G
Take off distance: 600 ft
Stall speed: 39 kt / 45 mph / 72 kmh
Landing speed: 54 mph
Cruising speed at 85%: 130 kt / 150 mph / 241 kmh
Vne: 196 kt / 225 mph / 362 kmh
Range w/45 minute res: 300 sm
Rate of climb at gross: 1000 fpm / 5 m/s
Takeoff run 500 ft
Take-off distance (50ft obstacle): 600 ft / 183 m
Landing roll 500 ft
Seats: 1
Undercarriage: tail wheel.
Service ceiling: 14,000 ft.
John T Monnett founded his company to sell plans and some compo¬nents for his Formula V Racer, the Sonerai, which was awarded the prize at the 1971 EAA convention at Oshkosh for the best single seat, Volkswagen engined aircraft.
1980: Monnett Experimental Aircraft, 955 Grace, Elgin, Il 60120, USA.
1982-3: Monnet Experimental Aircraft Inc, 895 W 20th Avenue, PO Box 2984, Oshkosh, Wiscon¬sin 54903, USA.
The APM 20 Lionceau began as the Moniot APM-20 in 1992, by Les Industries de Composites d’Auvergne Reunites (ICAR).
Designed by Philippe Moniot at Rex Composites and certified in 1999 EASA CS-VLA, the APM 20 Lionceau is a very light (400 kg empty, 634 kg loaded) and economical 73.5 kW (98.6 hp) Rotax 912 ULS powered aircraft is primarily intended to be used to learn to fly, but also to travel with a relatively high cruise speed (113 knots).
Manufactured by the French manufacturer Issoire Aviation, it is entirely built from composite materials, especially carbon fibers. Design (as Moniot APM-20) was started 1992 by Les Industries de Composites d’Auvergne Reunites (ICAR).
The design features a low wing, NACA 63618 aerofoil, thickness/chord ratio 18 per cent, dihedral 3o, incidence 2o, twist 1o. The structure is Carbon fibre/epoxy. Flying controls are conventional and manual. Spring elevator tab for pitch trim. Electrically operated slotted flaps to about two-thirds span. A refuelling point is on the port side of fuselage.
The landing gear is fixed tricycle type with spats; oleo-sprung steerable nose leg, composites main legs. Mainwheels and nosewheel diameter 330 mm; maximum pressure 2.35 bar (34 lb/sq in).
Two, side by side seats are under rearward-sliding tinted canopy. Dual controls standard. Baggage compartment at rear of seats. Fixed step forward of wing leading-edge on each side.
The prototype (F-WWMP) exhibited at Paris Air Show 1995 before first flight on 21 November 1995; third (second flying) aircraft (F-WWXX) exhibited statically at Paris Air Show, June 1997, fitted with JPX flat-four engine, which is not offered on production aircraft.
No.4 (also registered F-WWXX) was exhibited at Paris in June 1999 and No.5 (F-GRRE) in 2001.
They were certified to JAR-VLA on 17 May 1999 and to JAR-21 in 2000. The first all-carbon fibre, single-engine aircraft to gain JAR-VLA certification.
Development cost around FFr10 million. Unit cost FFr620,000, minimally equipped or FFr700,000 with standard equipment (2001). Operating cost FFr350 per hour (1998).
First flying in December 1995, the Issoire Aviation APM 20 Lionceau is entirely built from composite materials, especially carbon fibers. Production is carried out by Issoire Aviation.
The APM-22 Liondo was the prototype APM-21 F-WWMP equipped with large winglets and exhibited at Paris, 15-22 June 2003, as representative of this UAV proposal, with 24-hour endurance and 556 kg (1,225 lb) MTOW.
A three-seat version, the APM 30 Lion, was presented at the 2005 Paris Air Show.
Issoire APM-20 lionceau
Engine: Rotax 912A, 59.6 kW (80 hp)
Propeller: Evra AL1 two-blade, fixed-pitch wooden
Wingspan: 8.66 m (28 ft 5 in)
Wing area: 9.5 m2 (102 sq ft)
Aspect ratio: 7.9
Airfoil: NACA 63-418
Length: 6.6 m (21 ft 8 in)
Height: 2.4 m (7 ft 10 in)
Empty weight: 380 kg (838 lb)
Max takeoff weight: 620 kg (1,367 lb)
Fuel capacity: 68 litres (18.0 US gallons; 15.0 Imp gallons)
Usable fuel: 65 litres (17.2 US gallons; 14.3 Imp gallons)
Cruise speed: 230 km/h (140 mph, 120 kn)
Stall speed: 80 km/h (50 mph, 43 kn)
Never exceed speed: 250 km/h (160 mph, 130 kn)
Endurance: 4–5 hours
Rate of climb: 3.4 m/s (670 ft/min)
Seats: 2
APM-21 Lion
Engine: 73.5 kW (98.6 hp) Rotax 912 ULS engine
Propeller: two-blade, constant-speed Hoffmann
The first Mong Sport was built as a personal aircraft by the designer Ralph Mong, Jr, first flown on May 1, 1953 and plans for homebuilding were provided afterward, due to demand.
The original Mong MS1 Sport biplane was built around a Continental A65 65 hp (48 kW) engine. The biplane has an A frame shaped centre wing support. The biplane did not require expensive, drag producing support wires, using steel tubing instead. All Mong models use lift struts connected to the outer sections of the wings instead of flying and landing wires. Some builders installed the centre pylon support as an alteration to the design. But this alteration is not supported, recommended or condoned by Mong Aircraft. The fuselage is steel tube with aircraft fabric covering.
Costing approximately $1750 to build in 1971, original plans were still available for $100.00, plus shipping, out of the USA. Over 400 sets of plans for the aircraft had been sold.
Ed Fisher of Raceair Designs purchased the design rights in 1993 and designed a new set of wings that have 12 square feet more wing area, aimed at lower stall speeds. A new MS-3 airframe puts the control column under the longerons, which lowers the seat about 2″.
By 2019 Michael Stewart was owner of Mong Aircraft.
A Mong is a loop/roll/spin positive maneuver sport Biplane. For a sportplane Mong, recommended is the O-200 Continental for power.
In the mid-1960s, a biplane class was added to the Reno Air Races. The Mong Sport met the basic qualifications, and has been extensively modified over the years by builders to be used as a biplane racer. In 1965, Bill Boland won with his “Boland Mong” at 148 mph and again in 1967 and 1970 with speeds of 151 mph and 177 mph respectively. The Mongster won the 1968 Biplane class of the Reno National Championship. Long Gone Mong won in 1987 and 1989.
A highly modified Mong Phantom of Andrew Buehler and Tom Aberle with carbon fibre wings won in 2005 piloted by Andrew Buehler with 230,8 mph ( a 10 mph lead to the second place), and in 2006 with a speed of 251.958 mph, and has since raised the record to 284.454mph.
The Mong is the basis of the Micro Mong that Ed Fisher designed.
LSA Variant:
Green Sky Adventures Micro Mong
Mong MS1 Sport
Engine: 1 × Continental A65, 65 hp (48 kW)
Length: 14 ft 1 in (4.29 m)
Wingspan: 16 ft 10 in (5.13 m)
Height: 5 ft 6 in (1.68 m)
Wing area: 80 sq ft (7.4 m2)
Empty weight: 550 lb (249 kg)
Gross weight: 970 lb (440 kg)
Fuel capacity: 16 US gallons (61 litres)
Maximum speed: 100 kn; 185 km/h (115 mph)
Cruise speed: 96 kn; 177 km/h (110 mph)
Stall speed: 43 kn; 80 km/h (50 mph)
Service ceiling: 13,000 ft (4,000 m)
Rate of climb: 1,000 ft/min (5.1 m/s)
Crew: 1
MS1
Wing area: 80 sq. ft.
Empty weight: 560 lb
Fuel capacity: 8 USgal.
Stall speed: 60 mph
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 monoplane 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, 1.32×0.69m
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
A fully cantilevered aluminium wing folding for towing. HP range: 40-50.
The TU-10 Twin Eagle is a two-place ultralight trainer, semi-enclosed cockpit, high wing monoplane with Whitcomb winglets, 3-axis controls, trailing elevons. POWERPLANT: Rotax 447, reduction ratio 2.12:1, 52-inch prop. LANDING GEAR: Chrome moly aluminum tricycle. 1984 PRICE: $10,500.
In 1997 the Higher Planes T-10 kit price was US$11,500.
T-10
Engine: Rotax 447
Empty wt: 350 lbs
Max wt: 850 lbs
Wing span: 37ft 4in
Wing area: 176 sq.ft
Wing loading: 4.1 lbs/sq.ft
Power loading: 17.8 lbs/hp
Max speed: 63 mph
Cruise: 58 mph
Stall: 30 mph
Vne: 110 mph
Seats: 2
Engine: Rotax 503SC, 46 hp
Speed max: 78 mph
Cruise: 62 mph
Range: 200 sm
Stall: 35 mph
ROC: 650 fpm
Take-off dist: 190 ft
Landing dist: 200 ft
Service ceiling: 12,000 ft
Fuel cap: 6.5 USG
Weight empty: 400 lbs
Gross: 875 lbs
Height: 7.33 ft
Length: 9 ft
Wing span: 37.33 ft
Wing area: 170 sq.ft
Seats: 2
Landing gear: nose wheel
Glide ratio: 14-1
TU-10 Twin Eagle
Wingspan 37’4”
Wing area 170 sq.ft
Empty wt. 350 lbs
Gross weight 900 lbs
Cruise speed 60 mph
Stall speed 31 mph
Vmax 63 mph
Climb 500 fpm
Takeoff run 325 ft
Land¬ing roll 300 ft
Higher Planes Mitchell Wing T-10
Top speed: 78 mph
Cruise: 62 mph
Stall: 35 mph
Range: 200 sm
Rate of climb: 650 fpm
Takeoff dist: 190 ft
Landing dist: 200 ft
Service ceiling: 12,000 ft
Engine: Rotax 503-SC, 46 hp
HP range: 40-50
Fuel capacity: 6.5 USG
Empty weight: 400 lb
Gross weight: 875 lb
Height: 7.3 ft
Length: 9 ft
Wing span: 37.3 ft
Wing area: 170 sq.ft
Seats: 2
Landing gear: nose wheel
Glide ratio: 14-1
Single seat single engined mid wing monoplane with conventional three axis control. Wing has unswept leading and trailing edges, and constant chord; two fin tail. Pitch control by fully flying tail; yaw control by fin mounted rudders; roll control by full span ailerons also usable as flaps; control inputs through stick for pitch/roll and pedals for yaw. Wing braced from above by struts, wing profile NACA 23015; double surface. Undercarriage has three wheels in tricycle formation, with addi¬tional tailskids; steel spring suspension on nosewheel and glass fibre suspension on main wheels. Push right go right nosewheel steering connected to yaw control. Brake on nosewheel. Aluminium tube/wood/steel tube framework, with optional pod. Engine mounted above wing driving pusher propeller.
The P 38 was designed by Jim Meade and christened Lightning after the famous twin boom fighter of the Second World War. The prototype appeared at the end of 1980 and the first P 38 was sold during the second quarter of 1981. The prototype was fitted with a 26.0ft (7.92m) span wing having a 4.0ft (1.22m) chord, giving 104sq.ft (9.7 sq.m) of wing area using the same NACA 23015 profile as the B 10. With 200 lb (91 kg) empty weight and 450 lb (204 kg) maximum gross weight, this machine carried 250 lb (113 kg) useful load with a wing loading of 4.32 lb/sq.ft (21.1 kg/sq.m).
On the production models, the wing span was increased to 28.0ft (8.53m) and the chord also increased.
Initially fitted with a Honda Odyssey engine of 250 cc giving 20 hp, or as an option a Zenoah G25B also of 20 hp, the P 38 was in 1983 powered by the twin cylinder Cuyuna 430RR 30 hp engine. Its characteristics and performance figures do not allow its classification as an ultralight, so it is therefore necessary to hold at least a private pilot’s licence to fly the Lightning in the US.
The complete kit, requiring 80 h for assembly, has less than 200 pieces, the principal components being prefabricated and partly assembled. The wing ribs are wood, bonded with epoxy to the tubular Duralumin spar, while the leading edges are of polyurethane foam shaped and then covered with birch plywood. On the P 38, the ‘flaperons’ a combination of flap and aileron are made with ribs every 6 inch (15 cm). Like the other Mitchell models, this one is also available as an economy kit or as plans only.
Units delivered by June 1981 35 kits and plans.
The AG 38 is the crop spraying version of the P 38 Lightning, to which it is very similar except a pod is fitted. The prototype AG 38 was shown to the public during the EAA Convention at Oshkosh in August 1982. This aircraft is fitted with Micron X15 100 variable speed rotating nozzles, which are said to control droplet size and so reduce the amounts of chemical and water required. They are supplied from a shaped tank which carries 14.0 US gal (11.7 Imp gal, 53.0litre) of spray chemical. The tank is fitted under the seat and central wing section, between the legs of the main landing gear. An electric pump feeds the spray booms which are fitted with 19 fan nozzles across the full wing span. For a better spread, the two spray bars are placed at not the trailing edge as is usual, but 9.5 inch (24 cm) below the level of the wing.
At 50mph (80kph) the AG 38 spray swath varies from 20ft (6m) wide at 6ft (2m) altitude to 45 ft (14 m) wide at 15 ft (5 m) altitude. With the equipment set for maximum delivery, the AG 38 can deliver 48oz/acre (3.4 litre/hectare) and can treat 37 acre (15 hectare) per load. Reloading is required every 30 min, allowing an average coverage of 60 acre/h (24 hectare/h). At the other end of the scale, the machine can be set up for maximum acreage, when it will deliver 6oz/acre (0.42 litre/hectare) and treat 300 acre (120 hectare) per load. Reloading is required approximately every 2h, giving an average coverage of 140 acre/h (56 hectare/h).
P-38
Engine: Cuyuna 430RR, 35 hp at 5500 rpm
Power per unit area 0.29 hp/sq.ft, 3.1 hp/sq.m
Length overall 17.0ft, 5.18 m
Height overall 5.0ft, 1.52m
Wing span 28.0ft, 8.53m
Constant chord 4.3 ft, 1.29 m
Sweep forward 5 deg
Total wing area 120 sq.ft, 11.2 sq.m
Wing aspect ratio 6.5/1
Wheel track 5.0 ft, 1.52 m
Nosewheel diameter overall 10 inch, 25 cm
Main wheels diameter overall 10 inch, 25 cm
Empty weight 305 lb, 138kg
Max take off weight 700 lb, 317kg
Payload 395 lb, 179kg
Max wing loading 5.83 lb/sq.ft, 28.4 kg/sq.m
Max power loading 20.0 lb/hp, 9.lkg/hp
Load factors; +4.0, 4.0 ultimate
Max level speed 65 mph, 105 kph
Max cruising speed 55 mph, 88 kph
Stalling speed 32 mph, 51 kph
Max climb rate at sea level 500 ft/min, 2.5 m/s
Min sink rate 400 ft/min, 2.0 m/s
Best Wide ratio with power off 7/1
Take off distance 210ft, 64m
Landing distance 250ft, 76m
Service ceiling 12,000ft, 3660m
Range at average cruising speed 110 mile, 177 km
AG-38
Engine: Cuyuna 430RR, 35 hp at 5500 rpm
Power per unit area 0.29 hp/sq.ft, 3.1 hp/sq.m
Length overall 17.0ft, 5.18 m
Height overall 5.0ft, 1.52m
Wing span 28.0ft, 8.53m
Constant chord 4.3 ft, 1.29 m
Sweep forward 5 deg
Total wing area 120 sq.ft, 11.2 sq.m
Wing aspect ratio 6.5/1
Wheel track 5.0 ft, 1.52 m
Nosewheel diameter overall 10 inch, 25 cm
Main wheels diameter overall 10 inch, 25 cm
Empty weight 325 lb, 147kg
Max take off weight 700 lb, 317kg
Payload 375 lb, 170kg
Max wing loading 5.83 lb/sq.ft, 28.4 kg/sq.m
Max power loading 20.0 lb/hp, 9.lkg/hp
Load factors; +4.0, 4.0 ultimate
Max level speed 65mph, 105kph
Stalling speed 35mph, 56kph
Max climb rate at sea level 500ft/min, 2.5 m/s
Take off distance 275 ft, 85 m
Landing distance 325 ft, 100 m
Single seat single engined high wing monoplane 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; double surface. Undercarriage has three wheels in tricycle formation. Push right go right nosewheel steering connected to yaw control. Aluminium tube framework, with pod. Engine mounted below wing driving pusher propeller.
Shown in December 1982, the A 10 Silver Eagle is an updated version of the B 10 Mitchell Wing, not only as regards detail improvements, but in the technology and type of manufacture. Don Mitchell has abandoned the overhead stick, which comes down from the high wing on the B 10, to replace it with a conventional stick between the pilot’s knees. Materials (wood and fabric) used for the B 10 wing have been superseded by aluminium and a foam developed by NASA called honeyfoam and designated SR 502B, the final B indicating the use of boron.
The A 10 Silver Eagle was sold ready to fly and includes a fairing for the cockpit, wheel fairings on the main wheels, an upholstered seat with shoulder harness and an instrument panel. The price in April 1983 was $5995.
Ameriplanes Inc sold the Mitchell Wing A-10 described as a unique, ultralight motorglder for intermediate and advanced pilots based on Don Mitchell’s Mitchell Wing B-10 hang glider. It is a flying wing design from aluminium. It utilzes a Rotax 277/28 hp engine and was available in kit form for $9400 (does not include engine). Price completed in 2009: 11700 USD
The A-10 was available with a 2SI, A-20 engine and when equiped with same it comes in at 254lbs (the 103 UL limit). Other engines, like the Zenoah G25B-1 were also available.
The Higher Planes A-10 is stressed to +6 and –5.5 G, and the wings fold for transport. The kit price in 1997, without engine, was US$7900.
A-10
Engine: Zenoah 250 (242cc) 23hp
Static thrust: 160 lbs
Empty wt: 250 lbs
Wing span: 34’4”
Wing area: 134 sq.ft
Height: 6’2”
Length: 8’6”
Fuel cap; 3 USG
Construction: Aluminium, Boron, Foam
Max wt: 553 lbs
Stall speed: 27 mph
Max speed: 63 mph
Vne: 63 mph
Climb rate: 640 fpm @ 41 mph
Design limit: +5.5, -5.5g
Glide ratio: 15-1
Wing loading: 4.13 lbs/sq.ft
Power loading: 24.04 lbs/hp
Engine: Rotax 277, 26 hp
Speed max: 70 mph
Cruise: 55 mph
Range: 200 sm
Stall: 28 mph
ROC: 800 fpm
Take-off dist: 200 ft
Landing dist: 200 ft
Service ceiling: 12,000 ft
Fuel cap: 2.5 USG
Weight empty: 280 lbs
Gross: 553 lbs
Height: 7.33 ft
Length: 9.33 ft
Wing span: 34.33 ft
Wing area: 134 sq.ft
Seats: 1
Landing gear: nose wheel
A-10 Silver Eagle
Engine: Zenoah G2SB 1, 20 hp at 6500 rpm
Toothed belt reduction
Max static thrust 165 lb, 75 kg
Power per unit area 0.14 hp/sq.ft, 1.58 hp/sq.m
Fuel capacity 3.0 US gal, 2.5 Imp gal, 11.4 litre
Length overall 8.0ft, 2.43m
Height overall 5.6 ft, 1.67m
Wing span 34.4ft, 10.46m
Chord at root 6.0ft, 1.83m
Chord at tip 2.0ft, 0.61m
Dihedral 6 deg at tip
Sweepback 12 deg
Total wing area 136 sq.ft, 12.6sq.m
Wing aspect ratio 8.6/1
Nosewheel diameter overall 10 inch, 25 cm
Main wheels diameter overall 10 inch, 25 cm
Empty weight 250 lb, 113kg
Max take off weight 553 lb, 251 kg
Payload 303 lb, 138 kg
Max wing loading 4.06 lb/sq.ft, 19.8 kg/sq.m
Max power loading 27.6 lb/hp, 12.5 kg/hp
Load factors +6.0, 6.0 design
Max level speed 63 mph, 101 kph
Max cruising speed 58 mph, 93 kph
Stalling speed 26 mph, 42 kph
Max climb rate at sea level 650 ft/min, 3.3 m/s
Best glide ratio with power off 18/1
Take off distance 200ft, 60m
Landing dis¬tance 200 ft, 60 m
Ameriplanes Mitchell Wing A-10
Engine: Rotax 277, 28 hp
Wing span: 34.33 ft
Wing area: 156 sq.ft
Empty Weight: 115 kg / 254 lbs
MTOW Weight: 249 kg / 550 lbs
Stall: 24 kt / 28 mph / 45 kmh
Cruise: 52 kt / 60 mph / 97 kmh
VNE: 66 kt / 76 mph / 122 kmh
L/D: 16:1
Sink rate: 240ft/min.
Higher Planes Mitchell Wing A-10
Engine: Rotax 277, 26 hp
HP range: 22-26 hp
Top speed: 70 mph
Cruise: 55 mph
Stall: 28 mph
Range: 200 sm
Rate of climb: 800 fpm
Takeoff dist: 200 ft
Landing dist: 200 ft
Service ceiling: 12,000 ft
Fuel capacity: 2.5 USG
Empty weight: 280 lb
Gross weight: 553 lb
Height: 7.3 ft
Length: 9.3 ft
Wing span: 34.3 ft
Wing area: 134 sq.ft
Seats: 1
Landing gear: nose wheel
All Aero 