Goodyear racer number #95 the ‘Californian’ was built by Ed F. Allenbaugh, and flown by Dwight Dempster, both from North Hollywood, in the 1947 Goodyear races. Registered NX67893, it featured a fiberglass fuselage shell.
Engine: 85hp Continental C-85
Wingspan: 18’0″
Length: 14’11”
Seats: 1
The Allen Aircraft Engine Co. of Compton, a suburb of Los Angeles California, developed an eight-cylinder horizontally opposed aircraft engine during 1928–1929.
Little is known about this engine, other than that it was never given a Type Certificate and that it was not used on any known aircraft.
O-675
Type: 8-cylinder horizontally opposed
Bore: 4.75 in
Stroke: 4.75 in
Displacement: 673.4 ci
Dry weight: 575 lb
Cooling system: air-cooled
Ignition system: dual ignition
Power output: 200 hp@1800 rpm
The All American Aircraft 10-A Ensign (ATC 792) is an all-metal side-by-side two seat cabin monoplane with a large Plexiglas canopy enclosing the engine. Power is provided by an 85 hp Continental C85-12 engine, and the nosewheel of the fixed tri-gear is steerable.
Designed by Ernest Adler as an all-metal design with side-by-side cockpit under a bubble canopy, and knee-action tricycle gear, was a victim of the post-war slump.
First flown towards the end of 1945, the Model 10-A Ensign was designed and built by All American Aircraft Inc, a company previously specialising in sub-contract work for other manufacturers.
Priced at $3,495, at least four were built; NX14281, NX8003H, NC8004H, and NX90648.
A proposed production version was to have offered dual controls as optional.
Planned retractable-gear 125hp Model 10-D was canceled in the design stage.
Engine: Continental C85-12, 85 hp
Wingspan: 33 ft 0 in
Wing area: 138 sq.ft
Length: 21 ft 0 in
Height: 8 ft 6 in
Empty weight: 1000 lb
Loaded weight: 1550 lb
Max speed: 120 mph
Cruise: 110 mph
ROC: 700 fpm
Service ceiling: 12,000 ft
Range: 400 mi
Seats: 2
Alisport initiated development of the STOL YUMA in 1994. A single engine, two-seater side-by-side, high-wing monoplane with a metal structure, all aircraft structural parts are heat-treated and corrosion inhibiting coatings are used throughout. All aluminum skins are bonded to the underlying structure prior to final riveting.
The cockpit structure is a welded tubular steel frame, and aluminum is used for the wings, tail-cone, and empennage. The control surfaces are fabric-covered.
The flight characteristics of the YUMA are enhanced by an optimized wing profile and carbon-fiber leading edge slats (Handley-Page type) that directly address the requirements of S.T.O.L. flight. The large flaps permit steep final approaches to facilitate descent over tall obstacles.
The fuel system is two wing tanks and a header tank at the firewall providing a total endurance of up to five hours.
Engine: Rotax 912 UL (80 HP)
Wing span: 9,75 m
Cabin width: 1,18 m
Length: 6,45 m
Height: 2,45 m
Wheelbase: 2,00 m
Wing area: 13,4 sq.m
Aspect ratio: 6,6
Empty weight: 282 kg
Max takeoff weight: 450 kg
Wing loading: 33,5 kg/sq.m
Maximum speed: 175 kph
Cruise speed 75%: 150 Km/h
Stall (without flaps): 55 Km/h
Stall speed (with flaps): 50 Km/h
VNE: 105 kt / 121 mph / 195 kmh
Rate of climb: 6 m/s
TO dist (with 1 pob): 40 m
TO dist (full load): 45 m
Landing distance: 55 m
Max ceiling: 5000 m
Fuel capacity: 85 lt
Endurance max payload at cruise speed 75%(5000 rpm): 5,2 hr
Engine: Rotax 912 ULS (100 HP)
Wing span: 9,75 m
Cabin width: 1,18 m
Length: 6,45 m
Height: 2,45 m
Wheelbase: 2,00 m
Wing area: 13,4 sq.m
Aspect ratio: 6,6
Empty weight: 282 kg
Max takeoff weight: 450 kg
Wing loading: 33,5 kg/sq.m
Maximum speed: 185 Km/h
Cruise speed 75%: 160 Km/h
Stall (without flaps): 55 Km/h
Stall speed (with flaps): 50 Km/h
VNE: 105 kt / 121 mph / 195 kmh
Rate of climb: 8 m/s
TO dist (with 1 pob): 30 m
TO dist (full load): 40 m
Landing distance: 55 m
Max ceiling: 5000 m
Fuel capacity: 85 lt
Endurance with max payload at cruise speed 75%(5000 rpm): 4,5 hr
Engine: Rotax 914 UL (115 HP)
Wing span: 9,75 m
Cabin width: 1,18 m
Length: 6,45 m
Height: 2,45 m
Wheelbase: 2,00 m
Wing area: 13,4 sq.m
Aspect ratio: 6,6
Empty weight: 282 kg
Max takeoff weight: 450 kg
Wing loading: 33,5 kg/sq.m
Maximum speed: 195 Km/h
Cruise speed 75%: 170 Km/h
Stall (without flaps): 55 Km/h
Stall speed (with flaps): 50 Km/h
Rate of climb: 10 m/s
TO dist (with 1 pob): 30 m
TO dist (full load): 40 m
Landing distance: 55 m
Max ceiling: 7000 m
Fuel capacity: 85 lt
Endurance with max payload at cruise speed 75%(5000 rpm): 4,1 hr
The Silent Club is a light sailplane with 12-meter fiberglass wings for recreational flying. It has a blend of agility/control responsiveness, climb performance, safety, and fun. The two-position flaps have a reflex position to maintain good glide performance at higher airspeeds. The pure sailplane and fuel-injected self-launcher versions were available as quick-build kits. Assembly is simple, both due to all controls having fully automatic connections and due to the light weight of the wings. The airframe is built entirely of composite materials, with use of carbon fiber in the aft portions of the fuselage pod, the tail boom, and various critical locations of the structure. The cockpit is completely built of glass fibre. The Silent Club’s low sink rate and its stability while thermalling allow it to fly with hang-gliders and to be practically unbeatable in climb when compared with Standard class or 15m class sailplanes. It is easy to both launch and to land, and is particularly suitable for new pilots performing their first single-seat flights. The Silent Club has very efficient conventional air brakes and can be landed in less than 70 m (230 ft). Due to its span of only 12 m (39 ft) it can be stored in a small space. A fully enclosed “clam-shell” trailer is available for road transportation.
The Silent 2 is a high-performance light sailplane with 13-meter wings for recreational and sport flying.
The carbon-fiber wings have an elliptical planform, removable winglets, and five flap settings to cover the entire speed range. The pure sailplane and fuel-injected self-launcher versions were available as quick-build kits. Several World records have been set with the Silent 2 in the FAI Class-DU. A basic airframe combined with reasonable pilot weight will generally result in a take-off weight under the 220kg (485 lbs) maximum allowable required for the FAI’s DU Class. The Silent 2’s airframe is built entirely of composite materials, with use of carbon fiber in the aft portions of the fuselage pod, the tail boom, and various critical locations of the structure. The oven-cured wing structure includes extensive use of carbon-fiber. The sandwich skins use vacuum-bagged carbon fabric for the interior layer and glass fabric for the exterior layer while the wing spar uses pultruded carbon rods for the spar caps. It tows well behind trikes, sport-aircraft, and regular towplanes, making it versatile for all types of glider operations.
The Silent 2 TARGA is a high-performance light sailplane for recreational and sport flying. It has retractable landing gear, vertical-design winglets, and horizontal stabilizer with automatic trim. The pure sailplane and fuel-injected self-launcher versions were available as quick-build kits.
Powered by the proven Alisport A302efi engine producing 28hp at 6200rpm, this single-lever FADEC engine has electronic ignition, fuel-injection, electric start, and flywheel generator. The counterweighted monoblade carbon-fiber propeller has a swept diameter of 1.4m and electrically retracts into the fuselage along with the engine pylon. The wings have an elliptical planform, vertical design winglets, and a span of 13.3 meters. The wing structure includes extensive use of carbon fiber, both in the sandwich skins and in the tapered I-beam wing spar which uses pultruded carbon rods for the spar caps. The wing geometry is unique in that it varies non-linearly from the root to the tip, both in overall planform shape and in wing section profile. The flaperons stretch for 11.0 meters of the full wingspan and their range of motion varies from positive landing L, to +40 for thermalling, to 00, -40, and S reflex positions for cruising. The sailplane is trimmed in pitch via an innovative variable-position horizontal stabilizer. The stabilizer position is governed by the flaperon setting: the five settings of the flap control produce corresponding changes to the stabilizer incidence, thus defining the trim airspeed in relation to the flap requirements. The conventional elevator remains in trail, minimizing trim drag.
The Silent OP version has the engine mounted on a fixed pylon. Power is the Konig SD 570 or retractable Zanzoterra FZ 34 and single blade prop.
Silent
Light sailplane circa 1998.
Weight: 130 kg
Wing span: 12 m
Wing area: 10.3 sq.m
Vne: 200 km
Stall: 54km
Vz min: 0.6 m/sec
Glide Ratio: 32 @ 90 kph
Silent Club
Length: 20.8 ft.
Wingspan: 12m / 39.3 ft.
Wing area: 10.3sq.m / 110.9 sq.ft.
Aspect ratio: 14-1
Seats: 1
Cockpit width: 22 in
Empty wt: 135kg / 300 lbs.
Mtow: 240kg / 530 lbs.
Payload: 105kg
Cruise: 60 mph.
Stall: 36 mph
L/D: 31-1@ 85 km/h
Min sink: 126 fpm / 0.64 m/s @ 65 kph.
Structure: all composite
Silent Club Self-Launch
Engine: A302 EFI, 28 hp.
Length: 20.8 ft.
Wingspan: 39.3 ft.
Wing area: 110.9 sq.ft.
Aspect ratio: 14-1.
Seats: 1.
Cockpit width: 22 inch.
Empty wt: 375 lbs.
Mtow: 639 lbs.
Fuel cap: 4.5 USG.
Cruise: 53 mph.
Stall: 38 mph.
L/D: 31-1.
Min sink: 138 fpm.
Silent 2
Length: 20.8 ft.
Wingspan: 13m / 42.6 ft.
Wing area: 8.8sq.m / 94.7 sq.ft.
Aspect ratio: 19.2-1.
Seats: 1.
Cockpit width: 22 in
Empty wt: 125kg / 275 lbs.
Mtow: 245kg / 540 lbs.
Payload: 105kg
Cruise: 50 mph.
Stall: 37 mph.
L/D: 39-1 at 81 kph.
Min sink: 106 fpm / 0.54 m/s at 77 kph.
Structure: All composite
Silent 2 Electric
Engine: Air Energy DC, 13 kw.
Length: 20.8 ft.
Wingspan: 42.6 ft.
Wing area: 94.7 sq.ft.
Aspect ratio: 19.2-1.
Seats: 1.
Cockpit width: 22 in
Empty wt: 385 lbs.
Mtow: 660 lbs.
Cruise: 56 mph.
Stall: 40 mph.
L/D: 39-1.
Min sink: 118 fpm.
Silent 2 Self-Launch
Engine: A302 EFI, 28 hp.
Length: 20.8 ft.
Wingspan: 42.6 ft.
Wing area: 94.7 sq.ft.
Aspect ratio: 19.2-1.
Seats: 1.
Cockpit width: 22 in
Empty wt: 385 lbs.
Mtow: 660 lbs.
Fuel cap: 4.5 USG.
Cruise: 56 mph.
Stall: 40 mph
L/D: 39-1.
Min sink: 118 fpm.
Silent 2 Targa Self-Launch
Engine: Alisport A302efi 28 Hp single-cylinder air-cooled
Wing span: 13.3 m / 43.6 ft
Length: 20.8 ft.
Wing area: 8.9sq.m /95.7 sq.ft.
Aspect ratio: 20
Empty Weight: 185kg / 385 lbs.
Payload: 105kg
MTOW: 300kg / 660 lbs
Fuel cap: 4.2 USG
L/DMax: 40 at 90 km/h
MinSink: 0.60 m/s / 118 fpm @ 85km/h
Cruise: 56 mph
Stall: 40 mph
No. of Seats: 1
Cockpit width: 22 in
Silent OP
Engine: Konig SD 570, 28 hp
Wing span: 12 m
Wing area: 10.30 sq.m
MAUW: 270 kg
Empty weight: 165 kg
Fuel capacity: 2 x 20 lt
Seats: 1
Max speed: 200 kph
The Alfa is a European kit built aircraft designed by Heino Breditschka. An all-metal low-wing, tri-cycle gear airplane with side-by-side seating, the aircraft is 19.35 t in length and has a wing span of 29.5 ft. Suggested engine for the plane is a 110 HP Volkswagen Porsche G 2 2.400 air cooled boxer engine. The HB207 cruises at 140 kts with an fuel burn of 3.5 US Gal/hr and stalls (flaps down) at 40 kts. It features a 5 blade constant speed prop, retractable landing gear, and detachable wings.
The Alfa Romeo D2 was a nine-cylinder radial engine for aircraft use produced in Italy. It was typically rated between 240-270 hp. The engine was designed by Vittorio Jano and produced 600 units between 1931-1934. This engine was also first purpose-built aircraft engine produced by Alfa Romeo, before it all Alfa engines used in airplanes were derived from engines used in cars. A supercharged derivative was produced as the D2 C.
Applications:
Breda Ba.25
Caproni Ca.101
General characteristics
Type: Nine-cylinder radial engine
Bore: 120 mm (4.724 in.)
Stroke: 135 mm (5.315 in.)
Displacement: 13.74 L (838.5 cuin)
Supercharger: 2.5:1
Power output: 270 hp
Compression ratio: 5:1
The Alfa Romeo 135 Tornado was an Italian 18-cylinder radial engine designed by Giustino Cattaneo in 1934-35. The engine consisted of two nine-cylinder radial banks, similar to the Alfa Romeo 126. Cattaneo left Alfa Romeo in 1936, leaving the development to eng. Bossi and his staff. At the time of its first running in 1938 and 1939 it was the most powerful radial engine in the world, generating just less than 1492 kW (2000 hp) on 100-octane fuel, but the normal was 87 (1,200-1,600 hp).Despite the obvious potential, this engine was affected by many reliability problems. Reliability was solved in 1939 but it suffered from overheating and vibrations, so seriously that it was rejected from service. By 1944 only an handful were made, and never fitted in a operational aircraft. Only around 150 units of this engine were manufactured.Variants: 135 R.C.32Power output: 1177 kW (1600 hp) at Take Off, 1030 kW (1400 CV) at 3200m Applications:Cant Z.1018 “Leone” Savoia-Marchetti SM.87 (four planes) Savoia-Marchetti SM.82 (central engine) Savoia-Marchetti SM.90 (one prototype) Cant Z 1014 (five prototypes)135 R.C.34Power output: 1194 kW (1600 hp)Applications: Focke-Wulf Fw 200 “Condor” (engines supllied for testing) 136 R.C.25Power output: 1765 kW (2400 hp) at 0m, 1360 kW (1850 CV) at 2500mApplications: CRDA CANT Z.1018 “Leone”136 R.C.65Power output:1618 kW (2200 hp) at Take Off, 1214 kW (1650 CV) at 6500mType: 18-cylinder radial engine
Alfa Romeo built/designed several aircraft engines based on Bristol Jupiter and Pegasus designs. These engines were named as 125, 126, 128, 129 and 131. The 126-RC34 was derived from Bristol Pegasus and 126-RC35 from Jupiter 9-cylinder radial design. All these engines were mainly fitted to Italian bombers in World War II. Between 1934 and 1944 Alfa Romeo built around 11,000 units.
Alfa Romeo Jupiter (Bristol)
Power output: 313 kW (420 hp)
Applications:
Caproni Ca.97
Alfa Romeo 125 RC.35
Power output: 485 kW (650 hp)
Applications:
Breda Ba.64
Savoia-Marchetti SM.79 “Sparviero”
Savoia-Marchetti SM.81 “Pipistrello”
Alfa Romeo 126 RC.34
Power output: 507-582 kW (680-780 hp)
Applications:
DAR-10A (prototype)
Savoia-Marchetti SM.73
Savoia-Marchetti SM.74
Savoia-Marchetti SM.79 “Sparviero”
Savoia-Marchetti SM.81 “Pipistrello”
Savoia-Marchetti SM.83
Caproni Bergamaschi AP.1
Cant Z.506B “Airone”
Junkers Ju 52
Alfa Romeo 126 RC.32
Power output: 1,006 kW (1,350 hp)
Applications:
Savoia-Marchetti SM.79-II “Sparviero”
Alfa Romeo 126 RC.10 (civilian RC.34)
Power output: 559-597 kW (750-800 hp)
Applications:
Cant.Z.506A
Macchi M.C.94
Macchi M.C.100[5]
Savoia-Marchetti SM.73
Alfa Romeo 128 RC.18
1939
Power output: 641-717 kW (860-962 hp)
Applications:
Fiat G.12
Savoia-Marchetti S.M.79B “Sparviero”
Savoia-Marchetti SM.82 “Canguru”
Savoia-Marchetti SM.95
Alfa Romeo 128 RC.21
Power output: 708 kW (950 hp)
Applications:
Savoia-Marchetti SM.75 “Marsupiale”
Savoia-Marchetti SM.82
The Alfa Romeo 121 was an eight-cylinder, air-cooled, inverted V engine for aircraft use produced in Italy. It was typically rated at 280 kW (380 hp).
Applications:
Ambrosini S.7
Specifications:
Type: Eight-cylinder inverted V-8 air-cooled engine
Bore: 120 mm (4.72 in)
Stroke: 110 mm (4.33 in)
Displacement: 9.9952 L (609.9 in³)
Length: 1,780 mm (70 in)
Width: 684 mm (26.9 in)
Height: 700 mm (27.5 in)
Dry weight: 345 kg (760 lb)
Supercharger: Centrifugal type
Fuel system: Two horizontal carburettors, or one injection carburettor
Fuel type: 100/130 grade fuel
Oil system: Pressure type. One pressure and three scavenge pumps
Cooling system: Air cooling
Reduction gear: Spur gear type: reduction ratio 0.621:1
Power output: 284 kW (400 hp) at 3,000 rpm (take-off), 246kW (330 hp) at 3,000 rpm (max continuous power)
Compression ratio: 6.5:1
Specific fuel consumption: 290 g/hp/hr (0.63 lb/hp/hr) (take-off),
Oil consumption: 2.5 kg/hr (5.5 lb/hr)
Power-to-weight ratio: 0.82 kg/kW (0.53 hp/lb)
