Mitchell P-38 / AG-38

P-38

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.

Mitchell P-38 Article

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

Mitchell A-10

Mitchell A-10 Silver Eagle

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.

Mitchell Wing A-10

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

Mitchell B40F

A hang gliding fanatic, Dr H Long, gave Don Mitchell control of a high performance wing. By 1975 this same wing had become the B 10. The first powered version now carries the designation of B40F (F for foot launch).
The aircraft is in effect a wing, supporting beneath its lower surface a rigid frame formed by two sets of struts in the shape of an N, at the back of which is mounted a McCulloch Mc101 12hp engine with direct drive to a two blade pusher propeller.

The addition of a go-kart engine and streamlined pilot pod has turned the design into a high-performance ultralight. It is fast, sensitive and very maneuverable. The wing is wooden and built up in a typical “D” Section cantilever, with pilot cage attached underneath and a pusher prop in the rear. Top speed is about 55 mph, and climbout is around 350 fpm. It can be foot-launched, but the added weight of an engine and its accessories make it wise to consider tricycle gear. A Mac 101 engine swings a 42-inch prop and sips two gallons of gas in two hours.

Mitchell B-10 / XF-10

Single seat single engined high wing mono¬plane with conventional three axis control. Wing has swept back leading and trailing edges, and tapering chord; no tall. 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 NACA 23015; double surface. Undercarriage has three wheels in tricycle formation; suspension on all wheels. Push right go right nosewheel steering con¬nected to yaw control. Optional brake on nosewheel.

Mitchell B-10 Article

Aluminium tube/wood/steel tube framework, with optional pod. Engine mounted below wing driving pusher propeller.

A hang gliding fanatic, Dr H Long, gave Don Mitchell control of a high performance wing. By 1975 this same wing had become the B 10. The first powered version now carries the designation of B40F (F for foot launch).
The aircraft is in effect a wing, supporting beneath its lower surface a rigid frame formed by two sets of struts in the shape of an N, at the back of which is mounted a McCulloch Mc101 12hp engine with direct drive to a two blade pusher propeller.

Very quickly Don Mitchell fitted the framework with a tricycle undercarriage with a nosewheel steered by the rudder bar, while a more elaborate version of the B 10 was shown at Oshkosh in August 1981, fitted with a glass fibre fairing and main wheel spats. By 1980, more than 500 sets of plans or kits for the B 10 had been sold. Previously only sold as sets of plans or as a kit, the B 10 Mitchell Wing has been offered factory built, since September 1982.

The structure of each wing has five central ribs in a wooden lattice with six ribs on either side, all of quite conventional construction. The thick plywood spar has D shaped pieces of polyurethene foam resting on it every 4.3 inch (11 cm), which are then covered in 0.04 inch (l mm) thick sheets of plywood to form the leading edge. The control surfaces are made in the same way except for the rudders which have a tubular metallic spar. The covering is of Dacron or aviation quality Ceconite.

Due to the absence of a tail, roll and pitch control are both provided by stabilators, which span most of each half wing. Controlled from the stick, these stabilators act differentially like ailerons and together as elevators, while the rudders can also act as air brakes. The B 10 Mitchell Wing has dropped the Mc101 engine in favour of the Zenoah G25B. According to Mitchell Aircraft, con¬struction requires 250h of work. The 1983 prices are $6995 ready built, economy kit $1995 (without engine, instru¬ments and undercarriage), homebuilder’s kit $1295 (including raw materials and all hard¬ware but without engine, undercarriage, paint or glue), power pack $1595, tricycle undercarriage $495 and plans $125.

Units and plans delivered by June 1981 1,200 + kits.

Basically a strengthened B 10, the 1981 prototype of the XF 10 was originally shown by Mitchell Aircraft under the name of SR 10 and is a modified version of the B 10 Mitchell Wing, intended for the military market. This machine is today offered as a kit for an extra $1100 on top of the price of a B 10, compared with which the XF 10 is structurally reinforced and has a faired cockpit as standard. Like the standard B 10, the XF 10 uses the single cylinder Zenoah G2513 1.

Plans for the Mitchell wing B-10 became available from Richard Avalon at US Pacific, 892 Jenevein Ave., San Bruno, CA 94066. The B-10 has held world records by George Worthington. Richard worked with Don just before Don’s death and was not able to carry forward with some planned designs, but Richard is offering Don’s plans.

The Mitchell B-10J is a package available from Jim Gordon’s Micro Aviation. The US$5200 package includes a Garrett JFS100-13 originally used as a starter for the TF-41 engine in the A-7 Corsair. Including throttle package, lubrication and tailpipe assembly, the engine weight is 53 lb, and replaces the Zenoah. First flights were in February 1996, with 80 lb thrust.

Variation:
Bremner Mitchell B10 Wing Special

B-10
Engine: Zenoah G2SB 1, 23 hp at 6500 rpm
Propeller diameter 44 inch, 1.11 m
Toothed belt reduction, ratio 3.0/1
Max static thrust 165 lb, 75 kg
Power per unit area 0.17hp/sq.ft, 1.8hp/sq.m
Fuel capacity 3.0 US gal, 2.5 Imp gal, 11.4 litre
Length overall 6.0ft, 1.83 m
Height overall 4.0ft, 1.21m
Wing span 34.0ft, 10.36m
Chord at root 6.0ft, 1.83 m
Chord at tip 2.0 ft, 0.61 m
Dihedral (On outboard part of wing) 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, 25cm
Empty weight 185 lb, 84kg
Max take off weight 525 lb, 238kg
Payload 340 lb, 154kg
Max wing loading 3.86 lb/sq.ft, 18.8kg/sq.m
Max power loading 22.8 lb/hp, 10.3kg/hp
Load factors; +4.2 ultimate
Max level speed 55 mph, 88 kph
Max cruising speed 45 mph, 72kph
Stalling speed 25mph, 40kph
Max climb rate at sea level 300 ft/min, 1.5 m/s
Min sink rate 225ft/min at 35mph, 1.1m/s at 56 kph
Best glide ratio with power off 16/1
Take off distance 175ft, 53m
Landing distance 175 ft, 53 m
Service ceiling 12,000 ft, 3648 m
Range at average cruising speed 135 mile, 217 km

XF 10
Engine: Zenoah G2SB 1, 23 hp at 6500 rpm
Propeller diameter 44 inch, 1.11 m
Toothed belt reduction, ratio 3.0/1
Max static thrust 165 lb, 75 kg
Power per unit area 0.17hp/sq.ft, 1.8hp/sq.m
Fuel capacity 6.0 US gal, 5.0 Imp gal, 22.7 litre
Length overall 6.0ft, 1.83 m
Height overall 4.0ft, 1.21m
Wing span 34.0ft, 10.36m
Chord at root 6.0ft, 1.83 m
Chord at tip 2.0 ft, 0.61 m
Dihedral (On outboard part of wing) 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, 25cm
Empty weight 200 lb, 91kg
Max take off weight 600 lb, 272kg
Payload 400 lb, 181kg
Max wing loading 4.41 lb/sq.ft, 21.5 kg/sq.m
Max power loading 26.1 lb/hp, 11.8kg/hp
Never exceed speed 50mph, 80kph
Stalling speed 25mph. 40 kph

B-10J
Engine: Garrett JFS100-13, 80 lb thrust
Fuel burn: 10 USGPH
Fuel capacity: 3.5 USG
Endurance: 20-30 min

Mitchell Wing

A hang gliding fanatic, Dr H Long, gave Don Mitchell control of a high performance wing. It has aerodynamic control of external “stabilator” surfaces about all three axises through the use of a joystick. No weight shift is required. Spoilers are used to initiate a turn or to steepen the glide path for landing. Its extremely flat glide and low sink rate allow it to takeoff and land in almost ‘no wind’ conditions.

The wing is an all-wood structure with foam leading edge ribs. It has a single built-up C-spar with aircraft birch plywood torsion proof leading edge. The built-up truss ribs aft of the spar ar covered with seconite fabric.

The 8 ft 6 in outboard wing panels fold up over on top of the centre section for transportation. They may be removed as three pins connect outboard panels to the centre section.

The pilot is housed in a metal cage below the wing. Spoiler control is on the left, the control stick on the right. In flight the pilot goes into the supine position. A large clear mylar covering on the trailing edge above the pilot gives visibility overhead. The pilots cage folds up for ease in transportation.

In 1977 George Worthington flew an unpowered Mitchell Wing a straight distance of 107.8 miles.

By 1975 this same wing had become the B 10. The first powered version now carries the designation of B40F (F for foot launch).

The Mitchell was a rigid hang glider in wood, sold in plans. Two American companies were selling the rigid Mitchell. U.S Pacific sells plans and wood kits while Ameriplanes sells aluminium kits.

The 1976 wing was for advanced pilots. At lrast 20 service bulletins were to be applied to be safe.

Very pleasant in flight despite the strong reverse yaw but stable. The first 2 minutes are crucial because you have to understand everything quickly, the reverse yaw, the use of the rudders and the sensitivity of the handle on the pitch.

Wing area: 12.64 m²
Wing span: 10.2 m
Aspect ratio: 8.4
Hang glider weight: 35 kg
Minimum speed: 30 km/h
Maximum speed: 120 km/h
Max glide ratio (L/H): 16
Max glide ratio speed: 55 km/h
Minimum sink rate: 0.6 m/s

Wingspan: 10.36m
Wing area: 12.63m²
Weight: 37 kg – 39 with updates
VNE 120 km / h
Max. 100 km / h
Min speed: approx 30 Km / h
Max glide ratio (L/H): 16-18
Load: +6 -6G in free flight version (+4 -4 in ULM version)
Min fall rate: 0.6 – 0.8 m / sec

Wing span: 34 ft
Wing area: 136 sq,ft
Aspect ratio: 8.4
Weight: 68 lb
Takeoff speed: 14 mph
Stall speed: 11 mph
Max speed: 50 mph
Best glide ratio (L/D): 18-1
Best L/D speed: 32 mph
Min sink: 108 fpm

Mitchell Nimbus

Nimbus III

The Nimbus III was developed in 1956 by Don Mitchell from the earlier I and II models. Mitchell produced nine kits, of which four were completed. The prototype Nimbus III has a Gottingen airfoil and considerably less performance.

Nimbus III
Wing span: 12.19 m / 40 ft
Wing area: 9.85 sq.m / 106 sq.ft
Empty Weight: 204 kg / 450 lb
Payload: 100 kg / 220 lb
Gross Weight: 304 kg / 670 lb
Wing Load: 30.86 kg/sq.m / 6.4 lb/sq.ft
Aspect ratio: 14.7
Airfoil: Wortmann FX-05-191
L/DMax: 39 106 kph / 57 kt / 66 mph
MinSink: 0.73 m/s /2.4 fps / 1.42 kt
Seats: 1
Structure: all-wood, 3-piece wing

Mitchell

The Mitchell family of aircraft began in 1915, in Scotland, with the birth of Donald S. “Don” Mitchell. Hoping to create a better life for themselves, the family immigrated to the United States when the boy was only seven years old. He was still in school when he became fascinated with gliding. Indeed, Mitchell was a student at Alameda High School in Alameda when he built his first glider, under the tutelage of a pilot who had seen action during the First World War.

Intent on pursuing a career in aviation, Mitchell enlisted at the Boeing School of Aeronautics in Oakland.

In the 1930s, Mitchell worked for United Air Lines at Oakland and Fresno as a radio operator and station attendant. By now, however, he only dreamt of gliding. In spite of the Depression, Mitchell left his job in order to move south to San Fernando, near Los Angeles, where he visited glider pioneer William H. Bowlus – shop foreman at the factory which built Charles Lindbergh’ Spirit of St. Louis – and all but begged him to teach him how to design and build gliders.

Bowlus accepted and Mitchell trained under him for the next six years. All in all, Mitchell spent eleven years with Bowlus, working as his right-hand man on numerous projects during his last five years with his mentor. Along with another gentleman, the duo founded Bowlus Sailplane toward the end of 1936 and developed the BA-100 Baby Albatross glider, a very popular design with some structural problems, which was sold mainly if not exclusively in kits.

As the 1940s began, Mitchell designed and started to construct a large two-seat flying wing glider. To keep it under control without the usual tail, he developed a combination of aileron and elevator which he called a stabilator. All the while, Mitchell took part in demonstration flights for Bowlus Seaplane and was appointed soaring editor of Western Flying Magazine.

When he finally left Bowlus Sailplane, Mitchell went to teach aircraft welding at a technical institute located close by, at the Grand Central Air Terminal near Glendale. Leaving this position, he moved another short distance to the new Timm Aircraft factory in Van Nuys, where he helped with the molding of the fuselage of the S-160, a plastic-bonded wood basic trainer developed for use by the U.S. Navy and U.S. Army Air Corps. Mitchell later assisted the Civil Aeronautics Administration when the time came to perform the static tests of the aircraft. It passed with flying colours and later became, in April 1941, one of the first if not the very first ever plastic-bonded aircraft to receive an American Approved Type Certificate. The S-160 was later ordered by the U.S. Navy. Approximately 260 of these airplanes – now designated Timm N2T Tutors – were produced.

In early 1942, Timm Aircraft was awarded a U.S. Army Air Forces (USAAF) contract to build Waco CG-4 cargo gliders. Many other American companies received orders as well. Timm Aircraft eventually built close to 450 CG-4s. This aircraft turned out to be the most widely produced cargo glider in history.

His superiors at Timm Aircraft instructed Mitchell to organise construction of CG-4A wings in the factories of two furniture makers of the Los Angeles area. Weber Showcase, one of these manufacturers, soon hired him to take over control of their production. As all this was taking place, Mitchell nonetheless found the time to spend numerous evening and weekends with Bowlus to help with the design and construction of a pair of gliders – quite possibly two military transport gliders which proved eventually faulty under test and failed to win orders – as well as a half-size prototype of a large and rather unusual-looking transport glider designed as a private venture for the USAAF.

Confident that his design could help the war effort, Bowlus and an associate organised a company which finally became General Airborne Transport. Construction of a full-size prototype capable of carrying 42 soldiers or 10,000 pounds of freight, began. Mitchell left Weber Showcase in the spring of 1943 to work on this glider, all the while spending some time on his own flying wing design. Mitchell apparently became Director of Projects at General Airborne Transport. Sadly, the prototype of the CG-16 crashed in September 1943 during a test flight. Only Bowlus and one of the VIP passengers managed to parachute to safety. Still, the company managed to obtain permission to build a second prototype. An imposing-looking machine with good flying characteristics, the CG-16 nonetheless suffered from a number of design flaws. The program was cancelled in late 1944 and a third airplane was not built.

Following the end of the CG-16, Bowlus and a friend, Ted Nelson, started to work on a motorised version of the BA-100 Baby Albatross glider. The two of them formed Nelson Aircraft in San Fernando (California) to meet a perceived need for powered gliders now that the Second World War seemed about to end. Mitchell, who may helped with the design of the airplane, the Nelson Dragonfly, took part in the Civil Aeronautics Administration certification tests. Bowlus later appointed him supervisor of production.

In April 1946, after some years of work, Mitchell finally completed construction of his flying wing glider. After a number of successful test flights, Mitchell mounted a small engine on it and flew it as a powered airplane. In the meantime, the expected postwar light airplane boom was slowly turning into a bust and only a handful of Dragonflies left the factory. When the company closed its doors, Mitchell moved to San Leandro where he worked with Nelson and an associate on the design of new powered gliders. Their 1949 Nelson Hummingbird proved to be a better performer than the Dragonfly but its cost and relative lack of performance doomed it on the market. Only a handful were built.

As he worked on the Dragonfly, Mitchell set out on his own to build a new flying wing glider, which he called the Osprey, a single seat machine fitted with stabilators. Mitchell tested his flying wing several times near Oakland, in 1950. Unfortunately, the building in which the glider was stored burned to the ground and the flying wing was destroyed.

Faced with this, Mitchell threw himself into the design and construction of the Nimbus series of sailplanes. The Mitchell Nimbus III – which was developed around 1956 from the earlier Nimbus I and II – won the High Performance Sailplane Design Award at the 23rd National Soaring Contest held in Texas, as well as an award at the San Diego soaring meet.

During much of the 1960 and early 70s, Mitchell kept himself occupied by repairing and customising a number of aircraft. Around 1974, as interest in hang gliding was rapidly increasing, a Dr. Howard Long became intrigued by the idea of a flying wing hang glider. He asked Mitchell to build him such an aircraft. The first foot-launched Mitchell Wing hang glider, the first rigid-wing hang glider that could be controlled in roll, pitch and yaw, flew in 1976. Its flying characteristics and performance showed such promise that Mitchell received orders to build twelve after just one public demonstration flight.

Fascinated by the idea of capturing all the official records for hang gliding newly recognised by the Fédération aéronautique internationale, American champion sailplane pilot George Worthington bought the third one built and went on to set half a dozen world records between 1976 and 1981. Interest among enthusiasts was such that Mitchell organised Mitchell Wing – later Mitchell Aircraft – at Porterville (California). Orders came in from all over North America, Europe and beyond.

In the mid 1970s, Mitchell added a tubular structure and a small engine on one of his wings, turning it into a powered glider or ultralight airplane. A prototype first flew in 1976. The new powered model gained fame as the Mitchell B-10. Mitchell took his flying wings to the world famous fly-ins at Oshkosh and was awarded top honors on numerous occasions.

Design and construction of the U-2, an ultralight fitted with an enclosed nacelle for the pilot followed in 1979. In 1983, a Mitchell U-2 set a new world altitude record for aircraft weighting less than 270 kg with a climb to about 26,000, as well as a sustained altitude record of slightly less than 26,000 ft. The Mitchell P-38 flew later on.

May 1981

1983: Mitchell Aircraft Corp, 1900 South Newcomb, Porterville, California 93257, USA.
1984: 11616 W. 59th Street South, Sand Springs, OK 74063, USA.

Over the years, Mitchell has sold hundreds of drawings and kits for the B-10, the U-2, the P-38 as well as the hang gliding version of the B-10. The designations Mitchell gave to his creations were those of great American aircraft, i.e. the very modern Martin B-10 bomber of the 1930s, the highly distinctive Lockheed P-38 Lightning fighter of the Second World War and the famous Lockheed U-2 spy plane of the Cold War era.

Don Mitchell took ill and died in 1993.

Mississippi State University XV-11 Marvel

Students and researchers at Mississippi State University in Jackson built and flew the XV-11 Marvel in 1965 to test boundary layer and STOL technology. The name M.A.R.V.E.L. stood for “Mississippi Aerophysics Research Vehicle with Extended Latitude”.

The first all-composite aircraft, it carried out its initial program of research on behalf of the US Army in the late 1960s, and was rebuilt in the 1980s as a proof-of-concept for a utility aircraft.

The Marvel is now on permanent display at the Southern Museum of Flight at the Birmingham International Airport in Alabama.

Mirage Aircraft Celerity

The Celerity was designed by Larry Burton, who flew the prototype in 1985 and won an Oshkosh workmanship award that same year. The prototype has accumulated over 900 hours. It is designed to be built by the average person, with average skills, at low cost, yet perform as well as the most expensive kit airplanes in it’s class.

The Celerity is a high performance, 2-place side-by-side plans built airplane with fully retractable landing gear, including the tail wheel. It can also be built as the “Marathon” with fixed tricycle gear. Designed for builders with average skills, both aircraft are constructed from wood with fiberglass covering. Six construction videos were available. Celerity cruises in the 200 mph range on 150 to 180 hp and has an operating range of more than 750 miles with fuel reserve. The builder has the choice of carrying all the fuel in the wing, or sleek tip tanks can be installed.

Complete landing gear assemblies and other finished components were available from Mirage Aircraft.

Engine: Lycoming O-320, 160 hp
HP range: 150-180
Height: 5.5 ft
Length: 21 ft 10 in
Wing span: 25 ft
Wing area: 100 sq.ft
Weight empty: 1169 lb
Gross: 1800 lb
Fuel cap: 44 USG
Speed max: 220 mph
Cruise: 205 mph
Range: 1000 sm
Stall: 50 mph
ROC: 1800 fpm
Take-off dist: 800 ft
Landing dist: 1000 ft
Service ceiling: 20,000 ft
Seats: 2
Landing gear: retractable tail wheel