The 1927 VM-11 was built at Bettis Field, McKeesport, in association with Clifford Ball and D Barr Peat. It had a four-place cabin and open cockpit at the rear. It was registered N1540 c/n 11, which was later changed to N2972.
The VM-11 crashed on 3 November 1927.
Engine: 180hp Mercedes 6
Wingspan 38’2″
Length: 24’6
Seats: 5
The Technological Research Institute constituted the technical base on which Companhia Aeronáutica Paulista emerged. The Institute designed two aircraft that came to be manufactured in series by this company, in addition to designing the Paulistinha aircraft, it was the Paulistinha project, passed on to Companhia Aeronáutica Paulista (CPA) together with the Planalto plane that generated the first royalties paid to the IPT.
Neiva P-56 Paulistinha Article
Originally developed by Empresa Aeronáutica Ypiranga (EAY) as an unlicensed copy of the Taylor Cub powered by a Salmson 9Ad radial engine, the EAY-201 featured a high strut-braced wing, two enclosed tandem seats, and a steel-tube fuselage with fabric covering. Its tailwheel undercarriage was not retractable.
First flown in 1935, EAY had built five examples by the time that the firm was purchased by Companhia Aeronáutica Paulista (CAP) in 1942. CAP continued manufacturing the type under the designation CAP-4 with a 65 hp Franklin engine.
The Paulistinha was produced in three versions. The CAP 4 Tourer, the CAP 4B ambulance aircraft, and the CAP 4C military observation monoplane. The CAP 4C had a cut-down rear fuselage with the side windows extended aft.
Production of the Paulistinha was stopped in 1948, when the Paulistta company experienced financial difficulties, and resumed in 1956 by the Sociedade Construtora Aeronautica Neiva as the Pulistinha 56 (90 hp Continental C90-8F) and 56-B (100 hp Lycoming). The Paulistinha 56-C appeared in 1958, and 210 had been delivered by mid-1963. The Paulistinaha L-6 (100 hp Lycoming) was a liason version for the Brazilian Air Force, 19 being delivered in 1959.
The type was widely successful, with nearly 800 units being produced for Brazil’s flying clubs and armed forces, as well as for export to Argentina, Paraguay, Chile, Uruguay and Portugal. At the time of peak production in 1943, a new CAP-4 left the factory every day, and production continued until 1948 when the company enter financial difficulties.
In 1956, Sociedade Aeronáutica Neiva (Neiva) acquired the rights renaming it to P-56 Paulistinha, the design was used as the basis for an agricultural aircraft, the P-56 Agricola, adding a fibreglass chemical hopper and spraybars, but this was unable to compete with imported, purpose-built agricultural aircraft.
In dimensions and characteristics, it is similar to the last series of the Paulistinha CAP-4 produced by Companhia Aeronáutica Paulista , from which Neiva acquired the rights, launching a new version, named Paulistinha 56 or Neiva 56.
First flying in 1955, the Neiva P-56 Paulistinha could be equipped with a Continental C-90-8F or C90-12F engine, which could develop up to 115hp at 2625 RPM. A total of 256 were built
Its fuel system consists of two gas tanks, one at the top of the cabin and the other between the instrument panel and the engine fire wall, before entering the carburetor the gasoline passes through a filter and decanter type “cup” “.
The Brazilian Air Force operated this aircraft between 1959 and 1967, with the military designation L-6 . It was used in bombing connection, observation and calibration missions. Paraguayan Military Aviation bought four aircraft in the early 1960s. The Paraguayan Aeroclub bought four aircraft in the 1950s
In total about 840 were built.
Variants:
EAY-201
original version
Engine: Salmson 9Ad
Seats: 2
CAP-4 Paulistinha
main production version
Engine: 1 × Franklin 4AC, 48 kW (65 hp)
Wingspan: 10.10 m (33 ft 2 in)
Wing area: 17.0 m2 (183 sq ft)
Length: 6.65 m (21 ft 10 in)
Height: 1.95 m (6 ft 5 in)
Empty weight: 320 kg (705 lb)
Gross weight: 540 kg (1,190 lb)
Fuel capacity: 58 L (15 US gal; 13 imp gal)
Maximum speed: 155 km/h (96 mph, 84 kn)
Cruise speed: 140 km/h (87 mph, 76 kn)
Range: 500 km (310 mi, 270 nmi)
Service ceiling: 4,000 m (13,000 ft)
Rate of climb: 3.1 m/s (610 ft/min)
Crew: Two, pilot and instructor
CAP-4B
air ambulance version (2 prototypes built)
Engine: 1 × Franklin 4AC, 48 kW (65 hp)
Wingspan: 33 ft 2 in
Length: 21 ft 10 in
Height: 6 ft 4.75 in
Empty weight: 706 lb
Loaded weight: 1190 lb
Max speed: 96.5 mph
Cruise: 87 mph
ROC: 610 fpm
Range: 311 mi
CAP-4C
artillery-spotting version, (Paulistinha Rádio or Paulistinha Observação)
Engine: 1 × Franklin 4AC, 48 kW (65 hp)
Wingspan: 33 ft 2 in
Length: 21 ft 10 in
Height: 6 ft 4.75 in
Empty weight: 706 lb
Loaded weight: 1190 lb
Max speed: 96.5 mph
Cruise: 87 mph
ROC: 610 fpm
Range: 311 mi
P-56 Agricola
agricultural version by Neiva
60 built
Neiva P-56 Paulistinhab
Engine: Continental C90-8F, 90 hp
Wingspan: 10.8 m (35 ft 4 in)
Wning area: 183 sq.ft
Length: 6.90 m (22 ft 2 in)
Height: 1.95 m (6 ft 5 in)
Empty weight: 882 lb
MTOW: 1455 lb
Max speed: 100 mph at SL
Cruise: 90 mph
ROC: 875 fpm
Ceiling: 19,685 ft
Range: 560 mi
Endurance: 4 hrs
Neiva Paulistinha 56-C
Engine: Continental C-90-8F/12F, 90 hp (67 kW)
Seats: 2
256 built by between 1958 and 1964.
P56C-1 Paulistinha Rebocador
Paulistinha 56-D
Engine: Lycoming O-320-A1A, 150 hp (110 kW)
Single prototype built
Brazilian Air Force designated L-6A
No production.
The Eaves Cougar 1 is an American homebuilt aircraft that was designed by Leonard R. Eaves of Oklahoma City, Oklahoma and made available in form of plans for amateur construction.
The Eaves Cougar 1 was based upon the Nesmith Cougar and features a strut-braced high-wing, a two-seats-in-side-by-side configuration enclosed cockpit, fixed conventional landing gear and a single engine in tractor configuration.
The construction of the prototype was commenced in January 1957 at Eaves’ home in Oklahoma City. The design won third place in the 1963 Experimental Aircraft Association aircraft design competition. It was featured on the cover of Sport Aviation magazine in February 1963.
Eaves was killed in the crash of another homebuilt aircraft design on 3 March 2012 at age 92 and plans for the Cougar seem to be no longer available.
The aircraft is made from welded steel tubing and wood, covered in doped aircraft fabric. Its wing has a 23.25 ft (7.1 m) span and can be folded for storage or ground transportation. Engines used typically range from 85 to 125 hp (63 to 93 kW) but the airframe can accept engines as powerful as the 150 hp (112 kW) Lycoming O-320.
The aircraft has an empty weight of 700 lb (320 kg) and a gross weight of 1,400 lb (640 kg), giving a useful load of 700 lb (320 kg). With full fuel of 35 U.S. gallons (130 L; 29 imp gal) the payload is 490 lb (220 kg).
Cougar 1
Engine: 1 × Continental C85, 85 hp (63 kW)
Propellers: 2-bladed McCauley
Length: 18 ft 6 in (5.64 m)
Wingspan: 23 ft 4 in (7.11 m)
Empty weight: 700 lb (318 kg)
Gross weight: 1,400 lb (635 kg)
Fuel capacity: 35 U.S. gallons (130 L; 29 imp gal)
Maximum speed: 155 mph (249 km/h; 135 kn)
Cruise speed: 135 mph (117 kn; 217 km/h)
Stall speed: 60 mph (52 kn; 97 km/h)
Range: 400 mi (348 nmi; 644 km)
Rate of climb: 600 ft/min (3.0 m/s)
Crew: one
Capacity: one passenger
Leonard designed and built Skeeter, a two-place composite airplane, in the early 1960s, and test-hopped Skeeter in September 1966 at Wiley Post Airport.
Leonard R. Eaves, EAA Lifetime 2194, who lost his life in the crash of his Skeeter 1M homebuilt on Saturday, March 3, 2012. He was reportedly en route to a pancake breakfast in Ponca City, Oklahoma, when the crash happened on the Clarence E. Page Airport near Yukon, Oklahoma. Leonard was 92, and was survived by his wife, Rita.
This machine is a biplane of the Bleriot type, except that it has sliding planes at the wing tip for securing lateral stability. This machine has been making small jumps for a couple of weeks. It is equipped with a Ford automobile engine of 22 1/2 h.p., four-cylinder, water-cooled. The power plant weighs 200 pounds, and the whole machine 700 pounds, including the aviator. Warren S. Eaton was driving the machine when it went over on to its nose. It was running on the ground at the rate of 25 miles per hour when the front axle broke. As the tail was high in the air at the time, the tips of the skids stuck in the ground, and it ended up as shown. Mr. Eaton was thrown into the framework, but escaped unhurt.
First flown in 1994, the Paraproptor is partially manufactured in the US.
Cruise: 29 mph
Range: 100 sm
Rate of climb: 400 fpm
Takeoff dist: 15 ft
Landing dist: 2 ft
Service ceiling: 1000 ft
Engine: Koenig, 29 hp
HP range: 10-50 hp
Fuel capacity: 5 USG
Empty weight: 50 lb
Seats: 1
The Tyro is a high wing strut braced tail dragger. Construction is of aluminium with a constructed main spar, pressed ribs and stressed skin leading edge. Structual members are all bolted or pop riveted with no welding required. Covering is fabric material stretched over the frame. Undercarriage suspension has bungee rubbers on main wheels. Aircraft can be assembled and disassembled in seven minutes for storage and trailering. A cockpit pod has been included for pilot protection.
Mk.II
Engine: Rotax 447, 43 hp.
Prop: 68 cm x 28 cm pitch.
Wing span: 8.9 m, 10.5 sq m.
Length: 5.33m.
Weight: 113kgs.
Fuel capacity: 20 ltr.
Econ cruise speed: 56 kts.
Stall: l9kts.
Construction time: 100 hrs.
ROC 1100 fpm.
Side by side two-seater. Push right go right nosewheel steering connected to yaw control. Aluminium tube framework without pod. The prototype Snoop two seater was first shown in August 1982 at Oshkosh and was available as a kit requiring 40h for assembly. The wing has been enlarged compared with the Snoop and Snoop+.
The prototype was fitted with a Cuyuna 430R but the Eastern Ultralight brochures mention the Snoop II as being fitted with the new two cylinder ULII 02 from the same manufacturer, with a tuned exhaust and producing up to 45 hp. Not being classifiable as a microlight in the USA (its empty weight is 268 lb), this dual control two seater with centre mounted throttle needs a pilot who is a licence holder.
Gallery / Manuals / Snoop II Manual
Engine: Cuyuna ULII 02, 45 hp at 6200 rpm.
Engine: Cuyuna 430R, 40 hp.
Prop¬eller diameter and pitch 54×27 inch, 1.37 x 0.68 m.
Belt reduction, ratio 2.0/1.
Power per unit area 0.23 hp/sq.ft , 2.5 hp/sq.m .
Fuel capacity 5.0 US gal, 4.2 Imp gal, 18.9 litre.
Length overall 17.2 ft, 5.23 m.
Height overall 8.6ft, 2.59m.
Wing span 39.0ft, 11.88m.
Constant chord 5.0ft, 1.52m.
Dihedral 7 deg.
Sweepback 0 deg.
Total wing area 195sq.ft, 18.1sq.m.
Total spoiler area 3.0 sq.ft, 0.28 sq.m.
Rudder area 6.0 sq.ft, 0.56 sq.m.
Total elevator 6.0 sq.ft, 0.56 sq.m.
Wing aspect ratio 7.8/1.
Wheelbase 6.7 ft, 2.04 m.
Nosewheel diameter overall 12 inch, 30 cm.
Main wheels diameter overall 14 inch, 35 cm.
Floats, dimensions 11 x 2 ft, 3.35 x 0.61 m.
Skis, dimensions 4 x 1 ft, 1.22 x 0.30 m.
Empty weight 268 lb, 122kg.
Max take off weight 688 lb, 312kg.
Payload 420 lb, 190kg.
Max wing loading 3.52 lb/sq.ft, 17.2 kg/sq.m.
Max power loading 15.3 lb/hp, 6.9kg/hp.
Load factors +5.5, 3.5 design; +6.0, 4.0 ulti¬mate.
Max level speed 50 mph, 80 kph.
Never exceed speed 55 mph, 88kph.
Max cruising speed 45mph, 72kph.
Economic cruising speed 40mph, 64kph.
Stalling speed 17 mph, 27 kph.
Max climb rate at sea level 600ft/min, 3.0m/s.
Take off distance 100 ft, 30 m.
Landing distance 125 ft, 38 m.
Service ceiling 10,000 ft, 3050 m.
Range at average cruising speed 100 mile, 160 km.
Roll control by ailerons. Double surface wing with flaps. Presented at the Sun ‘n’ Fun in March 1983 the Snoop+ model differs from the Snoop by having a smaller span double surface wing fitted with ailerons and flaps. Like the earlier model, it also uses the Cuyuna ULII 02 with a tuned exhaust. The options are the same as those offered on the Snoop. As would be expected, the Snoop+ wing is much more costly to build than a single ¬surface design and as a result the Snoop+ cost exactly $1000 more than the Snoop: $5790 in 1982.
Engine: Cuyuna ULII 02, 35 hp at 6200 rpm.
Propeller diameter and pitch 54×27 inch, 1.37 x 0.68 m
Belt reduction, ratio 2.0/1.
Max static thrust 200 lb, 91 kg.
Power per unit area 0.23hp/sq.ft, 2.5 hp/sq.m.
Fuel capacity 5.0 US gal, 4.2 Imp gal, 18.9 litre.
Length overall 16.2 ft, 4.90 m.
Height overall 8.6ft, 2.59m.
Wing span 30.0ft, 9.14m.
Constant chord 4.0ft, 1.22m.
Dihedral 1deg.
Sweepback 0 deg.
Total wing area 150 sq.ft, 13.9sq.m.
Total aileron area 20.0sq.ft, 1.86sq.m.
Rudder area 6.0sq.ft, 0.56sq.m.
Total elevator area 6.0 sq.ft, 0.56 sq.m.
Wing aspect ratio 5.9/1.
Wheelbase 5.6 ft, 1.67 m.
Nosewheel diameter overall 12 inch, 30 cm.
Main wheels diameter overall 14 inch, 35 cm.
Floats, dimensions 9 x 2 ft, 2.74 x 0.61 m.
Skis, dimensions 3 x 1 ft, 0.91 x 0.30 m.
Empty weight 248 lb, 112kg.
Max take off weight 528 lb, 239 kg.
Payload 280 lb, 127 kg.
Max wing loading 3.5 lb/sq.ft, 17.1 kg/sq.m.
Max pow¬er loading 15.1 lb/hp, 6.82 kg/hp.
Load factors +5.5 3.5 design; +6.0, 4.0 ultimate.
Max level speed 60 mph, 97 kph.
Never exceed speed 63 mph, 101 kph.
Max cruising speed 55 mph, 88 kph.
Economic cruising speed 45mph, 72kph.
Stalling speed 25 mph, 40 kph.
Max climb rate at sea level 1000ft/min, 5.1m/s.
Take off distance 100 ft, 30 m.
Landing distance 150 ft, 45 m.
Service ceiling 10,000 ft, 3050 m.
Range at average cruising speed 175 mile, 281 km.
Single seat single engined high wing monoplane with conventional three axis control. Wing has unswept leading and trailing edges, and constant chord; cruciform tail. Pitch control by elevator on tail; yaw control by fully flying rudder; roll control by one third span spoilers; control inputs through stick for pitch/roll and pedals for yaw. Wing braced from above by kingpost and cables, from below by cables; wing profile single surface. Undercarriage has three wheels in tricycle formation; with additional tailskid; tension bar suspension on all wheels. No ground steering. No brakes. Aluminium tube framework, with optional pod. Engine mounted above wing driving pusher propeller.
Eastern Ultralights Snoop Article
The prototype of the Snoop single seater was shown at Sun ‘n’ Fun at Lakeland, Florida, in 1981, though at that time it had not made its first flight. At that time it was a two axis ultralight without spoilers and with a different structure and tail surfaces from the eventual production model. After several important modifications, it is today offered in the form of a kit requiring 30h for assembly, according to Eastern Ultralights.
At Sun ‘n’ Fun in March 1983, Eastern Ultralights announced the replacement of the Cuyuna 430R engine, previously standard on the Snoop, with the new ULII 02 from the same manufacturer. Options available are floats, skis, a pod, completely closed cockpit, wheel fairings, electric start and a strobe.
Price in 1982 $4790 as kit.
Engine: Cuyuna ULII 02
Max power 35 hp at 6200 rpm.
Prop¬eller diameter and pitch 54×27 inch, 1.37×0.68m.
V belt reduction, ratio 2.0/1.
Max static thrust 200 lb, 90.6 kg.
Power per unit area 0.21 hp/sq.ft, 2.3 hp/sq.m.
Fuel capacity 5.0 US gal, 4.2 Imp gal, 18.9 litre.
Length overall 16.2 ft, 4.90 m.
Height overall 8.6ft, 2.59m.
Wing span 33.0ft, 10.05m.
Constant chord 5.0ft, 1.52m.
Dihedral 7 deg
Sweepback 0 deg.
Total wing area 165 sq.ft, 15.3sq.m.
Total spoiler area 3.0sq.ft, 0.28sq.m.
Rudder area 6.0 sq.ft, 0.56sq.m .
Total elevator area 6.0 sq.ft, 0.56 sq.m.
Wing aspect ratio 6.6/1.
Wheelbase 5.6 ft, 1.67 m.
Nosewheel diameter overall 12 inch, 30cm.
Main wheels diameter overall 14 inch, 35 cm.
Floats, dimensions 9 x 2 ft, 2.74 x 0.61 m.
Skis, dimensions 3 x 1 ft, 0.91 x 0.30 m.
Empty weight 238 lb, 108kg.
Max take off weight 518 lb, 235kg.
Payload 280 lb, 127kg.
Max wing loading 3.2 lb/sq.ft, 15.3 kg/sq.m.
Max pow¬er loading 14.8 lb/hp, 6.7 kg/hp.
Load factors +5.5, 3.5 design; +6.0, 4.0 ultimate.
Max level speed 50 mph, 80 kph.
Never exceed speed 55 mph, 88 kph.
Max cruising speed 45 mph, 72 kph.
Economic cruising speed 40 mph, 64 kph.
Stalling speed 18 mph, 29 kph.
Max climb rate at sea level 600ft/min, 3.0m/s.
Take off dist: 75 ft, 23 m.
Landing distance 100 ft, 30 m.
Service ceiling 10,000 ft, 3050 m.
Range at average cruising speed 125 mile, 201 km.
