Offers plans (1976) to construct JC-01 and more-powerful (and nosewheel undercarriage) JC-200 two-seat low-wing monoplanes.
Post WW2
Costello Flapper
Australian Ron Costello, 46, of Victoria, designed and built this pedal-powered flapper in 1964. The tail is controlled ‘string’, with the pilot standing on a narrow platform.
Costello worked for the Civil Aviation Department and government buddies notified him officially by letter that man-powered craft don’t always work.
Cosmic Aircraft Corp
USA
In May 1970 Cosmic Aircraft Corp acquired all rights in manufacture of F-23 single-seat agricultural monoplane, produced previously by D. D. Funk Aviation Company Inc. Two models: F-23A (Continental radial) and F-23B (Jabobs radial). Production ceased 1975.
Corby CJ-1 Starlet
The Starlet was designed by Australian aero engineer John Corby of Sydney, N.S.W, Australia, for a competition held by English company Rollason Aircraft Ltd in 1964. The design was placed eighth, although it became first from the competition to be built. The prototype (VH-CBS) first flew on August 9th, 1967.
The Corby Starlet is a semi-aerobatic sports aircraft made of an all-wood onstruction.
The fuselage is a combination of spruce longerons and frames and is sheeted with plywood. The wing is a single-piece structure, consisting of a solid laminated spar and built-up ribs. The remainder of the wing, including the ailerons, is open-structure and fabric covered. The D-nose leading edge is plywood covered. The main undercarriage consists of spring-steel legs bolted to a stiffened frame in the fuselage, immediately behind the firewall. An 8 Imp. gallon fuel tank is located in the fuselage, immediately behind the firewall.
Powered usually by a VW conversion, the Starlet will take any suitable engine up to 75 hp and 72 kg (160 lb) in weight, and is aerobatic with limitations of +4.8 and 1.8G. Fuel consumption in the Starlet is between 10 and 14 litres per hour, depending on the power settings used, with an economic cruise of 110 knots. The Starlet can carry 15 lbs in a locker behind the seat, still normally within centre of gravity limits. Extra freight in most single seat homebuilts is usually either worn or sat upon to keep the C of G in the same place. Economic cruise is around 85 knots. At almost full throttle (3400 revs) the aircraft will approach VNE (138kts). The stall in a glide came at 35 knots.
Some Starlets have been outfitted with 2180’s (75-80 hp) and these cruise at VNE (185) and climb at 1900 fpm.
Corby CJ-1 Starlet
Engine: VW or Jabiru
Horsepower: VW 45 – 75 hp Jabiru 80 hp
Propeller: Wood 54 inch
Overall Length: 15.1 ft (4.6 m)
Height: 4.8 ft (1.46 m)
Wingspan: 18.5 ft (5.63 m)
Wing Area: 68.5 sq ft (6.36 sq m)
Wing Loading: 10.9 lbs/sq ft (4.9 kg/sq m)
Cabin Width: 21.75 inch (.55 m)
Empty Weight: 450 lbs (203.6 kg)
Gross Weight: 750 lbs (339.4 kg)
Useful Load: 300 lbs (135.7 kg)
Fuel Capacity: 11.1 gal (42 l)
Maximum Speed: 139 kts @ sea level
Cruise Speed: 113 kts
Stall (or Min.) Speed:@ gross weight 30 kts
Service Ceiling: 14,500 ft (4419 m)
Takeoff Distance: 350 ft (106 m)
Landing Distance: 450 ft (137 m)
Rate of Climb (gross): 1000 fpm
Maximum Range: 425 nm
“G” Loading: +4.5g (+6.75g ultimate), -4.5g
Landing Gear: FG (Tailwheel)
Seats: 1
Corby Starlet
Engine: VW conversion, 70 hp
Engine range: 160 lbs or less 75 hp
Fuselage Length: 14 ft 9 in
Height: 4 ft 10 in
Width: 21.75 in
Span: 18 ft 6 in
Wing Area 68.5 sq.ft
Wing loading 10.2 lb/sq.ft
Power loading 11.6 lbs per hp
Empty Weight 450 – 500 lbs
Gross weight one piece wing: 750 lbs
Gross weight two piece wing: 650 lbs
Takeoff distance 350 ft
Landing distance 450 ft
Fuel capacity 11 gals US/ 9.7 Imp. Gals/44 lbs/20 kg
Stall (power off) 35 mph
Top speed (level) 160 mph
Normal Cruise 115-130 mph
Fuel burn Cruise 3.5 gph US / 21 lbs per hr
VNE (Mph) 159 (tested to 185)
Rate of Climb 850 fpm
Range 425 sm
Servive ceiling: 14,500 ft
Roll Rate 270 dps (approx.)
Take-off dist 50 ft: 1200 ft
Landing dist 50 ft: 1200 ft
Design Load +/- 4.5 proof (+/- 6.75 ultimate) Utility or Semi Aerobatic
MAC 45 in
Incidence 2.5 deg – 1 deg Tip
Airfoil: NACA 43012A
Aileron Deflection +15 deg – 15 deg
Horizontal tailplane
Span: 6 ft 6 in
Area: 13.75 sq. ft.
Elevator deflection +30 deg – -20 deg
Vertical Tailplane
Area: 7.4 sq. ft.
Rudder Deflection +/- 25 deg
Horsepower range: 30 to 60
Engine Weight 130-160 lbs
C.G. Range: 20 – 25% MAC or 8.7 in to 11.4 in” aft of Wing LE
Number of Seats:
One Building Time: 1400+
Engine: Agusta, 42 h.p.
Span: 18’ 6”.
Length: 14’ 9”.
Wing Area: 68.5 sq. ft.
Empty Weight: 400 lb.
Loaded Weight (semi-aerobatic): 650 lb.
Wing Loading: 9.2 lb/sq. ft.
Max. Speed: 115 mph.
Cruise Speed: 104 mph.
Engine: VW, 60 hp.
Vne: 160 mph.
Cruise: 130 mph.
Range: 425 sm.
Stall: 35 mph.
ROC: 1000 fpm.
Take-off dist: 350 ft.
Landing dist: 450 ft.
Service ceiling: 14,500 ft.
Fuel cap: 11 USG.
Weight empty: 450 lbs.
Gross: 750 lbs.
Height: 4.8 ft.
Length: 15.1 ft.
Wing span: 18.5 ft.
Wing area: 68.5 sq.ft.
Seats: 1.
Landing gear: tail wheel.
Corben Junior Ace / Ace Aircraft Junior Ace
The Junior Ace is lightweight, easy to build, fun to fly and requires minimal maintenance. It has been modified from the original Corben Baby Ace so that it can utilize aircraft engines. The fuselage has also been widened, the horizontal stabilizer was modified for easier construction and modern aircraft wheels and brakes are now called for. With nearly a 34 ft wingspan and Clark Y airfoil, the Pober Junior Ace, designed by EAA founding president Paul Poberezny, is docile in stall and landing patterns. Airframe is 4130 steel tubing, wings are all wood and the recommended powerplant is a Continental C-85. Empty weight of the Junior Ace is 750 pounds and gross capacity is 1,320 pounds.
The Pober Junior Ace made its first flight with Captain Bud Judy at the controls. This first flight was successful and displayed the short field capabilities as well as low stall speed – ideal for small airstrips. The drawings for the airplane have full size wing rib drawings and two types of ailerons – the Friess aileron being a bit more responsive and lighter on aileron control. The indicated stall speed with one person on board is approximately 36 mpg. Indicated cruise with the Continental C-85-8 was a little over 80 mph. The Pober Junior Ace is open cockpit. The fuselage is chromoly steel tube, the tail group is chromoly steel tube and flat sheet stock to form ribs. The landing gear is chromoly tube with coil spring shocks. Wings are spruce spars and ribs. Two place side by side.
The kit price in 2009 was US$20950.
Junior Ace E
Engine: 85hp.
Span: 26’5”.
Wing area: 112 sq.ft.
Length: 17’9”.
Max wt: 1150 lbs.
Empty wt: 640 lbs.
ROC: 500 fpm.
Cruise: 78 kts.
Seats: 2.
Pober Junior Ace
Engine: Continental C-85, 85 hp.
HP range: 85-125.
Speed max: 130 mph.
Cruise: 80 mph.
Range: 250 sm.
Stall: 38 mph.
ROC: 500 fpm.
Take-off dist: 350 ft.
Landing dist: 450 ft.
Service ceiling: 25,000 ft.
Fuel cap: 12 USG.
Weight empty: 750 lbs.
Gross: 1320 lbs.
Height: 7.33 ft.
Length: 20 ft.
Wing span: 34 ft.
Wing area: 168 sq.ft.
Seats: 2.
Landing gear: tail wheel.
Engine: Lycoming O-235.
Hp range: 65-125.
Wingspan: 26.5 ft.
Length: 17.9 ft.
Wing area: 110 sq.ft.
Empty wt: 700 lbs.
Mtow: 1320 lbs.
Fuel cap: 22 USG.
Cruise: 100 mph.
Stall: 44 mph.
Range: 410 sm.
Roc: 500 fpm.
To dist: 600 ft.
Ldg dist: 300 ft.
Cockpit width: 40 in.
Ace Aircraft Corben Junior Ace Model E
Engine: Continental, Lycoming
Horsepower: 85-120
Propeller: 2 blade metal or wood
Cabin Width: 30 or 36 inches (76 or 91 cm)
Gross Weight: 1320 lbs (600 kg)
Empty Weight: 700 lbs (345 kg)
Useful Load: 620 lbs (270 kg)
Fuel Capacity: 22 USG (83 l)
Wingspan: 26.5 ft (8 m)
Wing Area: 110 sq.ft (10.2 sq.m)
Wing Loading: 12 lbs/sq.ft (58.6 kg/sq.m)
Overall Length: 18 ft (5.49 m)
Maximum Speed VNE: 113 kt | 130 mph | 209 kmh @ sea level
Cruise Speed: 95 kts
Stall Speed(@ MTOW): 38 kt | 44 mph | 71 kmh
Service Ceiling: 10,500 ft (3,200 m)
Takeoff Distance: 600 ft (183 m)
Landing Distance: 300 ft (91.5 m)
Rate of Climb(gross): 500 fpm
Center Of Gravity Aft Limit: 18.36″
Center Of Gravity Forward Limit:11.88″
Empty Cg: 12.5″ To 13.5″
Incidence Angles: Reference: Upper Longeron
Horiz. Stab: 0.0 Degrees
Wing: +1.18 Degrees
Engine: 0.0 Degrees Vert./Hor.
Vertical Fin: 0.0 Deg. (Fuse C/L)
Control Surface Travel Ailerons: 20 Deg. Up/Dn
Elevator: 32 Deg. Up/Dn
Rudder: 27 Deg. L/R
Center Of Gravity Aft Limit=18.36″
Forward Limit=11.88″
Empty Cg= 12.5″ To 13.5″
Incidence Angles: Reference= Upper Longeron
Horiz. Stab.= 0.0 Degrees
Wing= +1.18 Degrees
Engine= 0.0 Degrees Vert./Hor.
Vertical Fin= 0.0 Deg. (Fuse C/L)
Control Surface Travel Ailerons: 20 Deg. Up/Dn
Elevator: 32 Deg. Up/Dn
Rudder: 27 Deg. L/R
Landing Gear: FG (tailwheel or trike)
Seats: 2 Side-by-Side
Acro SportInc Pober Junior Ace
Engine: Continental C-85, 85 hp
HP range: 85-125 hp
Top speed: 130 mph
Cruise: 80 mph
Stall: 38 mph
Range: 250 nm
Rate of climb: 500 fpm
Takeoff dist: 350 ft
Landing dist: 450 ft
Service ceiling: 25,000 ft
Fuel capacity: 12 USG
Empty weight: 750 lb
Gross weight: 1313 lb
Height: 7.3 ft
Length: 20 ft
Wing span: 34 ft
Wing area: 168 sq.ft
Seats: 2
Undercarriage: tailwheel
Corben Baby Ace / Ace Aircraft Baby Ace
The Corben Baby Ace of 1929 was a professional design based on the Heath Parasol, but was a little more comfortable and had much better performance because of higher power. A 40-hp French Salmson AD-9 was used. Only six were factory-built, and a few were built from magazine plans in the 1930s.
The original Corben Baby Ace first flew back in 1931.
A single seat, high wing, sport plane powered by a modified Ford Model A 4 cyl inline engine. A simple and conventional design of open cockpit, strut-braced wing and tailplane, and a fixed, strutted, undercarriage. Later up-dated and marketed as the Pober Super Ace.
In 1954, Paul Poberenzy, who a year earlier had founded the still fledgling Experimental Aircraft Association, built a Baby Ace aircraft as a three part series in Mechanix Illustrated. The success of the articles caused an explosion in the homebuilt movement. The Baby Ace that Mr. Poberenzy built for Mechanix Illustrated is now in the EAA AirVenture Museum.
The Baby Ace was extensively redesigned in 1955 as an ultralight monoplane specially designed for the amateur builder, the Baby Ace Model D. Baby Aces usually carry Continental engines rated from 65 to 85 hp and their performance is considered excellent by owners. Construction consists of a steel tube fuselage, all-wood wings and fabric covering. The wing is Clark Y mod from the root to the tip.
The Model C was refined by Ed Jacobs as the Model D. This first flew, as the DuCharme/EAA Baby Ace, on 16 November 1956.
In 1961 Ace Aircraft Mfg Co (Edwin T Jacobs), McFarland WI, purchased Baby Ace rights from Cliff DuCharme, West Bend WI.
Plans offered in 1968 for single-place Baby Ace ($28.50) and two-place Junior Ace, or Model E ($36.50). The kit price in 2009 was US$18950.
Variation:
Dunn D-1
Specifications:
Engine: Szekley, 40 hp
Wingspan: 28 ft 8 in
Length: 17 ft 5 in
Height: 6 ft 0 in
Speed: 85 mph
Seats: 1
Baby Ace Model D
Engine: Continental C-65, 65 hp.
Hp range: 65-120.
Gross Wt. 950 lb.
Empty Wt. 575 lb.
Fuel capacity 17 USG.
Wingspan 26 ft 5 in
Length: 17 ft 9in
Wing area: 112 sq.ft.
Top 110 mph.
Cruise 90-100 mph.
Stall 34-38 mph.
Climb rate 1200 fpm.
Takeoff run 200ft.
Landing roll 250 ft.
Range 350-400 sm
Cockpit width: 34 in.
Seats: 1.
Ace Aircraft Corben Baby Ace Model D
Engine: Continental, Lycoming
Horsepower: 65-100
Propeller: 2 blade metal or wood
Cabin Width: 24 inches (61 cm)
MTOW Weight: 950 lbs (430 kg)
Empty Weight: 575 lbs (260 kg)
Useful Load: 375 lbs (170 kg)
Fuel Capacity: 17 USG (64 lt)
Wingspan: 26.5 ft (8 m)
Wing Area: 110 sq.ft (10.2 sq.m)
Wing Loading: 8.6 lbs/sq.ft (42 kg/sq.m)
Overall Length: 17.9 ft (5.46 m)
Maximum Speed VNE: 96 kts | 110 mph | 177 kmh @ sea level
Cruise Speed: 87 kts | 100 mph | 161 kmh
Stall Speed(@ MTOW): 30 kts | 34 mph | 55 kmh
Service Ceiling: 10,500 ft (3,200 m)
Takeoff Distance: 300 ft (91.5 m)
Landing Distance: 250 ft (76 m)
Rate of Climb(gross): 1200 fpm | 6 m/s
Centre of Gravity Aft Limit: 18.36 in
Centre of Gravity Forward Limit: 11.88 in
Empty Cg: 12.5 in To 13.5 in
Incidence Angles: Reference: Upper Longeron
Horiz. Stab: 0.0 Degrees
Wing: +1.18 Degrees
Engine: 0.0 Degrees Vert./Hor.
Vertical Fin: 0.0 Deg. (Fuse C/L)
Control Surface Travel: Ailerons: 20 Deg. Up/Dn
Elevator: 32 Deg. Up/Dn
Rudder: 27 Deg. L/R
Landing Gear: FG (tailwheel or trike)
Seats: 1
Corben
Orland G. “Ace” Corben designed and marketed the first homebuilt aircraft kit beginning in 1923; the “Baby Ace”; followed by the “Junior Ace,” the “Cabin Ace” and the “Super Ace!”
The Ace Aircraft Manufacturing Company was established in Wichita, Kansas in 1929 by Orland Corben to market the world’s first homebuilt aircraft, a machine of his own design called the Baby Ace. The enterprise did not last long before US regulations changed to restrict homebuilt aircraft, and Corben was forced to stop marketing his design.
He next commenced operations in Madison, Wisconsin in 1931 under the name Corben Sport Plane and Supply Company and produced a prototype sports plane known as the Super Ace. This endeavor soon languished, and the company remained dormant until Paul Poberezny purchased its assets for $US 200 in 1952. This included plans to three aircraft designs and a variety of components.
Poberezny was one of the founders of the Experimental Aircraft Association in 1953 and was approached by Mechanix Illustrated magazine the following year to write a series of articles on building an aircraft at home. Their publication caused considerable demand for plans, but Poberezny felt compelled to divest himself of marketing them in order to avoid any potential conflict of interest with his position within the EAA.
Since then, the rights have changed hands several times. They were purchased from Poberezny by Cliff Du Charme of West Bend, Wisconsin, who sold them to Edwin T. Jacob of McFarland, Wisconsin in 1961. Mr. Jacob sold them in 1965 to Thurman Baird of Asheville, North Carolina, who also owned the rights to the American Flea and the Heath Parasol aircraft. The rights were purchased from Baird’s estate in 1986 by Denny Meadows of Chesapeake, West Virginia, who sold them to Bill Wood of Toccoa, Georgia in 1998.
The Corben Aces have been modernised and refined by Paul Poberezny, Cliff DuCharne, Thurman Baird, Denny Meadows and others over the years. These aircraft are still being built, flown.
Bill Wood, the owner of the Ace Aircraft Company, at Toccoa Georgia Airport (KTOC) maintains the marketing and kit production.
Cook JC-1 Challenger
John Cook was trained in England and emigrated to the US to work on aircraft when the UK industry imploded in the 60’s. After stints at several companies including Helio, he went to work for Northrop on the 747 (Northrop designed and built the center and aft fuselage) and after work in the evenings and on weekends, several co-workers went down to Torrance and helped production design this plane in return for stock in the company. They built a prototype and a static test article, intending to obtain an FAA Type Certificate. The aircraft first flew in May 1969 and performed well; it passed static tests with very minor fixes. During a spin test, the FAA pilot kept the power on during the first turn of the spin – we had always closed the throttle as it stalled – and the plane entered an unrecoverable spin mode. John and the FAA pilot parachuted to safety, but the plane N21CA fell into the LA Harbor.
They built a second prototype, N72CA first flying in November 1971, and John Cook and John Parker test flew it to determine a safe aft CG limit. During one of these tests in January 1972 they got into the same situation and bailed out. JP was fine but Cook’s parachute was hit by the spinning plane and he was killed.
The company continued for a while and a third prototype was first flown in 1972 (N123CA) and an attempt was made to market the project as a homebuilt. This was not successful, the company folded and the plane was sold.
Cook Aircraft Corp
Founded by John A. Cook in 1968 at Torrance, California, to market JC-1 Challenger four-seat cabin monoplane. Two prototypes built (first flight May 1969). Third prototype flew November 1971, but crashed January 1972, killing Cook. Company continued, hoping for certification with a fourth (modified) aircraft, first flown 1972, but activities ceased in mid-1970s.
Convertawings Model A / Quadrotor
As the result of Convertawings’ further developmental work on this four rotor configuration, a first prototype was completed in 1955 and it has flown successfully.
The four rotors of this helicopter are mounted laterally on outriggers in two tandem pairs. The four rotors were positioned in an “H” configuration, and the design incorporated simplified hubs with strap-mounted blades, a form of “hinge-less” rotor. The control mechanism is extremely simplified and obtained by differential change of thrust between the rotors. There is no cyclic control, but only collective control. In the experimental prototype the fuselage was of tubular steel, the booms supporting the rotors in aluminium alloy. Power is provided by two engines connected to the rotor drive system by multiple vee belts. Shafting and transmission cases ensure inter-connection between the four rotors, so that either engine can drive all of them. There is a tricycle undercarriage with two wheels in the rear section and a nose wheel which can swivel.
The first flights took place in March 1956, flown by its designer and test pilot, D.H.Kaplan. Despite successful testing and development, military support for the Quadrotor ceased after cutbacks in defense spending.
The Quadarotor A was a small test vehicle for the Projecled 60-76 passenger Model E Quadrotor on the same general lines. The Model E is intended to have four R-1820 piston-engines or Dart turboprops, mounted directly under the rotors.
However, the design – particularly its control system – was a precursor of future experimental vertical-rising aircraft.
Model A
Engines: 2 x Continental 0-90, 90hp
Rotor diameter: 5.92m / 15 ft
Gross weight: 998kg / 1,950 lb
Number of seats: 1
