The Cranwell CLA.3 was designed to compete in the 1925 Lympne light aircraft trials, a high-wing braced monoplane powered by a Bristol Cherub engine.
July 1925 saw the first flight of the CLA.3, registered G-EBMC.
It won the International Speed Race at Lympne when it achieved 86.92 mph. It was re-engined in 1926 with a Bristol Cherub III.
The CLA.3 was scrapped in 1929.
Engine: Bristol Cherub
Wingspan: 21.00 ft
Length: 18.06 ft
The Cranwell CLA.2 was a two-seat single-engined biplane designed and built for the 1924 Lympne light aircraft trials.
It was first flown at Cranwell at 14 September 1924 with a Bristol Cherub as G-EBKC, it went on to win the £300 Reliability Prize at Lympne.
After the light plane trials the CLA.2 went to RAF Martlesham Heath for evaluation but it was written off by an Air Ministry pilot. The Air Ministry compensated the club for the loss and this was used to fund the next project.
Engine: Bristol Cherub
Wingspan: 29.08 ft
Length: 23.03 ft
The Cranwell Light Aeroplane Club was formed in 1923 by staff and students of the RAF College Cranwell to design and build light aircraft. One of the members was Flight Lieutenant Nicholas Comper who became the Chief Designer. Comper and the club designed and built four aircraft with the last three types being flown.
The Cranwell CLA.1 (a single bay, single seater biplane) was the first attempt by the Club to design an aircraft but was never built. This was followed by the CLA.2, CLA.3, and CLA.4, which were built.
Nicholas Comper went on to form Comper aircraft.
A single-seat primary glider designed and built by Cramlington Aircraft Ltd, Northumberland. Conventional wooden construction, it featured easy dismantlement. The fuselage consisted of a rigid boom to tail-unit. Originally designed with a wing chord of 5 ft, this was reduced to 4 ft 6 in as a cost reduction.
The undercarriage was a main skid only. The wing was wire braced with no flaps or airbrakes.
The price in 1930 was £55.
Specifications published in a 1930 ‘Sailplane and Glider’ gave a wingspan of 10.21 m / 33 ft 6 in, and length of 5.18 m / 17 ft 0 in.
Later specifications given were;
Wingspan: 10.41 m / 34 ft 2 in
Length: 5.58 m / 18 ft 3.5 in
Wing area: 14.21 sq.m / 153 sq.ft
Aspect ratio: 7.6
Empty weight: 63.5 kg / 140 lb
Seats: 1
The Cranfield Institute of Technology had a design study for a competition class aerobatic aircraft to represent Britain in the World Aerobatics Contests.
A company, Air Invert, was set up between the Institute and Alan Curtiss to produce the aircraft. The prototype was allocated registration G-BCIT, c/n 001.
The Cranfield Institute of Technology had a design study for a competition class aerobatic aircraft. The result was the Cranfield A1.
A plans and kits two-seat high-wing monoplane.
USA
Has offered plans and kits to build the Craft Aerotech 200 two-seat and twin-engined rotorcraft, and the 200 FW two-seat high-wing monoplane.
Single seat single engined mid wing mono¬plane with conventional three axis control. Wing shape; tapering chord; no tail, canard wing. Pitch control by fully flying canard; yaw control by tip rudders on canard; roll control by half span ailerons. Cantilever wing; wing profile; double surface. Aluminium fuselage. Engine mounted at wing height driving pusher propeller.
The Cozza/Scholl Scorpion was only an experimental machine in 1982.
Chicago based designers Craig Cozza and Mark Scholl wanted to create an ultralight with good soaring ability and which would operate safely in temperatures low enough to weaken composites. So the Scorpion uses an all aluminium construction, with Dacron wing covering. Pitch control is by fully flying canard and yaw control by tip rudders mounted on the ends of the canard. Half span ailerons look after roll control.
Particularly novel is the wing construction which allows the pilot to rig the aircraft with 40.0 ft (12.19 m) wings for soaring, or to halve the span by removing a 10.0 ft (3.05 m) panel from outboard end of each wing, in which form the Scorpion will have a more ultralight-like feel. For ease of construction, the fuselage is triangular in cross section, allowing flap panels to be used.
The low drag shape has allowed the designers to use a small engine, and they have chosen the single cylinder Cuyuna 215R of 20 hp for the prototype.
Engine: Cuyuna 215R, 20 hp.
Wing span 20.0 or 40. ft (6.10 or 12.19m).
Empty weight 235 lb, 107 kg.
Max cruising speed 60mph, 97kph.
Cozy is designer Nat Puffer’s side-by-side version of Burt Rutan’s Long¬EZ. It has a larger instrument panel, full dual controls, a large baggage compartment and the same efficiency, speed and range as Long-EZ, allowing passenger to assist with piloting/navigating, and makes long trips more pleasant and less fatiguing, as well as adding a margin of safety in bad-weather flying.
The Cozy MK IV is a high-performance, four-seat canard aircraft which is comfortable, efficient, and economical to build. It has a range of about 1,000 miles and a top speed of 200 mph. When constructed according to plans and operated within the approval C.G. range, the canard configuration makes it highly resistant to stalls or loss of position control. The MK IV features full dual control and two-axis trim. The composite construction is very strong, resistant to corrosion and fatigue. The MKIV features the same moldless construction as the Cozy. It used the same basic materials of foam, glass, cloth, and epoxy.
AeroCad Inc also licence manufacture a development of the Cozy as the AeroCanard.
Aircraft Spruce & Specialty Co. has acquired all existing inventory, tooling, and drawings for the prefabricated metal parts used in construction of the popular Cozy III and Cozy Mark IV aircraft as of January 1, 2004. Ken Brock Manufacturing Co. of Stanton, CA produced the metal parts for the construction of the Cozy and Long-EZ aircraft since the mid-1970’s until ceasing business operations on December 31, 2005. As the owner of the design rights for the Cozy Mark IV and the source for plans and kits, Aircraft Spruce continues to sell Brock’s parts. There was no remaining inventory of some of the parts, but there are new alternate sources on most of them.
These designs are protected with U.S. copyrights, and Aircraft Spruce has licensed no one else to copy all or any part of these designs to sell, loan, or give to others.
Greg Richter converted his Cozy III from a Mazda RX7 motor car engine to General Electric T58 turbine jet engine power. The transformation was performed by Valerie Harris and Robert with EZJET at Covington, Tennessee, in 1991.
CO-z Development Cozy Article Nov 83
Cosy Classic
Engine 118-hp Lycoming 0-235.
Wingspan 26.1 ft
Gross Wt. 1500 lb.
Empty Wt. 850 lb
Fuel capaci¬ty 52 USG
Cruise (75 percent) 180 mph.
Climb rate (solo) 1500 fpm
Climb rate (gross) 900 fpm.
Takeoff run (solo) 670 ft
Takeoff run (gross) 1050 ft.
Range 1800 miles
Cosy Classic
Engine: Lycoming O-320, 160 hp.
HP range: 150-160.
Speed max: 225 mph.
Cruise: 187 mph.
Range: 1000 sm.
Stall: 67 mph.
ROC: 1500 fpm.
Take-off dist: 1480 ft.
Landing dist: 1640 ft.
Service ceiling: 20,000 ft.
Fuel cap: 52 USG.
Weight empty: 960 lbs.
Gross: 1750 lbs.
Height: 7.8 ft.
Length: 17.7 ft.
Wing span: 26.33 ft.
Wing area: 95.6 sq.ft.
Seats: 3.
Landing gear: retractable nose wheel.
Cosy III
Speed max: 225mph.
Cruise: 190 mph.
Range: 1000 sm.
ROC: 2000 fpm.
Take-off dist: 1500 ft.
Landing dist: 1500 ft.
Service ceiling: 20,000 ft.
Engine: Lycoming O-320, 160 hp.
HP range: 150-160.
Fuel cap: 52 USG.
Weight empty: 960 lbs.
Gross: 1750 lbs.
Height: 7.8 ft.
Length: 17 ft.
Wing span: 26.1 ft.
Wing area: 95.6 sq.ft.
Seats: 3.
Landing gear: nose wheel.
Cozy Mark IV
Engine: Lycoming O-360 180 hp.
Wing Span: 28.1 ft
Wing area: 88.3 sq.ft
Canard Span: 12.6 ft
Canard Area: 14.7 sq.ft
Length: 16.9 ft
Height: 7.9 ft
Cabin W/H: 42/39in
Max. front seat: 400 lbs.
Empty wt: 1050 lbs.
Gross wt.: 2050 lb
Take-off solo/gross: 1200/1700 ft.
Climb solo/gross: 2000/1200 fpm
Cruise 75% 8000 ft: 220 mph
Cruise 40% 12000 ft: 185 mph
Max. range 75%: 1000 mi
Max. range 40%: 1300 mi.
Ceiling: 20,000+ ft.
Ldg.Dist.solo/gross 1000/1300 ft.
Cozy Mark IV
Engine: Lycoming O-360A, 180 hp.
HP range: 160-180.
Height: 7.9 ft.
Length: 16.9 ft.
Wing span: 28.1 ft.
Wing area: 88.3 sq.ft.
Speed max: 220 mph.
Cruise 75% 8000 ft: 220 mph.
Cruise 40% 12,000 ft: 185 mph.
Range 75%: 1000 sm.
Range 40%: 1300 sm.
ROC SL: 1200 fpm.
Take-off dist: 1700 ft.
Landing dist: 1200 ft.
Service ceiling: 20,000 ft.
Fuel cap: 52 USG.
Weight empty: 1050 lbs.
Gross: 2050 lbs.
Seats: 4.
Cabin width: 42 in
Cabin height: 39 in
Front seats max: 400 lb
Landing gear: retractable nose wheel.
Cozy / Mk.IV
Engine: Lycoming
Wing span: 8.56 m
Wing area: 9.41 sq.m
MAUW: 930 kg
Empty weight: 476 kg
Fuel capacity: 197 lt
Max speed: 354 kph
Cruise speed: 306 kph
Minimum speed: 108 kph
Climb rate: 10 m/s
Seats: 4
Plan price (1998): $500
Kit price (1998): $14,000
