In 1918, Adamoli and Cattani designed the smallest possible single-engine seat fighter around the most powerful rotary engine available, the 200-hp (149-kW) Le Rhone. With conventional wooden construction and fabric covering, the fighter was unequal-span unstaggered biplane with Warren truss-type interplane bracing. Lateral control was by interlinked and hinged wing leading edges varing the wing’s camber tip. Rigid tubes were used to actuate the movable tail surfaces. Construction of the prototype Fighter began at the Farina works in Turin, but was then transferred to the Officine Moncenisio in Condove for completion. Initial static testing revealed that the engine only developed 160hp (119 kW) and the fighter would be seriously underpowered. These limited trails took place at the end of WW1 and further development of the fighter was abandoned after the Armistice.
Adamoli-Cattani fighter (estimated for fully-rated engine) Type: single-seat biplane fighter Engine: 160-hp (149-Kw) Le Rhone rotary Maximum level speed: 186mph (300 kmh) Endurance: 2 hr 30 min Empty weight: 1,035 lb (470 kg) Loaded weight: 1,488 lb (675 kg Wing span: 28 ft 2 ½ in (8.6 m) Length: 20 ft 1/8in (6.1 m) Armament: 2 x 0.303-in (7.7mm) machine guns
The 1930 B-4 of J.Adams was a single place overhead wing monoplane powered by a Henderson motorcycle engine. Registered N742Y, it was possibly a modified Pietenpol.
Created by Burt Rutan and first flown on 21 March 2000 (pilot Glenn Maben), the fuselage seats six, in between a tractor and a pusher engine, each of 350 hp.
The airfoil is the NASA LS(1)-0417 from root to tip.
The RA-17 was a special version for use as ag-plane with spraying equipment under the wings and the chemicals hopper in the fuselage, making it a single-seat aircraft. Only a prototype was built which was modified from the second RA-15/1, and the sole RA-17 made a first flight on June 2, 1949.
A side-by-side two-seater, the RA-15 Major was externally and dimensionally similar to the RA-14, but had a plywood covered fuselage, a much larger vertical tail and also featured improved systems.
The first example made its maiden flight on April 13, 1947. Engine in the RA-15 was a 75 hp Régnier 4D-2.
RA-15/1
The RA-15/1 Major was similar to the RA-15, but powered by a 65 hp Continental A65 engine.
RA-15 Major Engine: 75 hp Régnier 4D-2 Wingspan: 34 ft 9 in Length: 22 ft 11 in Empty weight: 616 lb Loaded weight: 1145 lb Max speed: 109 mph Ceiling: 16,400 ft
A side-by-side two seater, the RA-14 Loisirs was mainly intended for construction by amateur builders and aero clubs, using Adam-supplied parts and components. The RA-14 was also delivered complete.The RA-14 made the first flight on March 16, 1946 and this aircraft was powered by a 40 hp Train engine. The RA-14 had a fabric covered fuselage and wings and was built in several variants, with engines in the 65-90 hp power range. The type was popular in the immediate post-war years and several dozens were built.
One example of the RA-14S Loisirs was built, featuring a plywood covered fuselage and several other features of the RA-15 model. In 1957 Maranda Aircraft in Canada acquired the marketing rights for the RA-14 and also developed several improved versions. The RA-14 serving as the basis of the AMF S-14. Another homebuilt variant was available from Falconar, also in Canada.
USA Markets plans, and some components for the Aero-Sport single-seat aerobatic/competition biplane and Super Acro-Sport for unlimited aerobatics, two-seat Aero-Sport II aerobatic biplane, Pober Junior Ace two-seat parasol-wing monoplane, Pober Pixie and Pober Super Ace single-seat parasol-wing monoplanes, and Nesmith Cougar I two-seat high-wing cabin monoplane.
The Acrolite 2M aircraft was designed in 1991 and built in 1991 to 1994, it had its first flight in June of 1994. It is a high wing two place tandem seat monoplane powered by a Rotax 582, 65 hp engine. Originally designed for the Rotax 912, performance is surprisingly good with the smaller engine. It was designed as per TP10141 the Canadian specifications for advanced ultralight aircraft and also meets the U.S. Sport Pilot requirements. The aircraft is stressed for this category with a 4 g. limit load and 6 g. ultimate load. The aircraft was designed with strength, ability to take abuse, ease of repair, good short field performance and stable flight characteristics as the most important features with aircraft grade materials used throughout. Tandem seating was selected and most of the popular ultralight twin cylinder two stroke engines can be used from 60 hp on up and the lighter four cylinder aircraft engines like the 80 hp four cylinder Rotax 912 and the 80 hp Jabiru. With an engine of 65 hp or more the aircraft is easily capable of carrying two 180 lb persons of over 6 ft. in height and full fuel. The fuselage is long for better stability and is constructed of welded 4130 chrome moly steel as per standard aircraft methods and covered with Polyfiber 1.7 oz. fabric. The tail assembly is constructed of 6061 aluminum tube riveted together with 2024-T3 aluminum gusset plates and fabric covered. This type construction allows a full cantilever empennage with low drag and light weight. Control linkages to the ailerons and elevator are push-pull rods with bearings on each end for positive control and friction free operation. Rudder and steerable tailwheel control is via a common cable. The wing is of stressed skin construction with a box section main spar, a channel section rear spar and strut braced. It is built entirely of 2024-T3 aluminum, fully sheeted and flush riveted with 1/8 inch diameter stainless steel blind rivets. The ailerons are full span aluminum tube, fabric covered and static balanced. The landing gear is one piece spring aluminum clamped and bolted directly to the bottom of the fuselage with four bolts. This type landing gear has low drag is easy to construct and handles hard landings and rough ground well. The wheels and tires are 600 X 5 aircraft type with cable operated drum brakes. Optionally hydraulic operated disk brakes can also be used. Floats and skis can also be used with a minimum of adapting. On November 2002 the 582 engine was removed for installation in the new Triplane and a new Rotax 912U engine was purchased for it. During the next year the 912 engine was installed, modifications were made to the airframe to strengthen the landing gear area, the fuselage was recovered, wheel fairings were added and the aircraft was painted. The first flight with the new engine was made on Nov. 8, 2003. A set of skis were fitted and flew it on skis through the winter of 2004/2005. After over 200 hours on the airframe, all the restrictions had been flown off and the flight testing had been completed, and the construction drawings and builders manual were completed and the design offered for sale.
Engine: Rotax 912, 80 hp Reduction: 2.23 to 1 Propeller: 68 x 48 Airfoil: GA30U-412 Wingspan: 28.4 ft Wing area: 141 sq.ft Wing chord: 5 ft Aspect ratio: 5.7 to 1 Length: 20.3 ft Height: 6.5 ft Fuel capacity: 14 gal U.S. Wheel & tire size: 600 x 6 Empty weight: 600 lb Gross weight: 1200 lb Span loading: 20.0 lb/ft Wing loading: 8.5 lb/sq.ft Power loading: 15 lb/bhp Power off stall speed: 44 mph Power on stall speed: 40 mph Landing speed: 60 mph Maneuvering speed: 85 mph Maximum level speed: 130 mph Never exceed speed: 150 mph Cruise speed: 110 mph@ 5000 rpm Best glide speed: 75 mph Best rate of climb: 1100 fpm Best climb rate speed: 80 mph Range: 250 sm Take off distance: 750 ft Landing distance: 500 ft Cockpit width: 30 in
Engine: Rotax 618, 75 hp Reduction: 2.58 to 1 Propeller: 66 x 46 Airfoil: GA30U-412 Wingspan: 28.4 ft Wing area: 141 sq.ft Wing chord: 5 ft Aspect ratio: 5.7 to 1 Length: 20.3 ft Height: 6.5 ft Fuel capacity: 14 gal U.S. Wheel & tire size: 600 x 6 Empty weight: 575 lbs Gross weight: 1100 lbs Span loading: 18.7 lb./ft Wing loading: 7.8 lb/sq. ft. Power loading: 14.7 lb/bhp Power off stall speed: 42 mph. Power on stall speed: 38 mph Landing speed: 57 mph Maneuvering speed: 85 mph Maximum level speed: 125 mph Never exceed speed: 150 mph Cruise speed: 105 mph@ 5800 Best glide speed: 75 mph Best rate of climb: 1000 fpm Best climb rate speed: 80 mph Range: 250 sm Take off distance: 750 ft Landing distance: 500 ft
Engine: Rotax 582, 65 hp Reduction: 2.58 to 1 Propeller: 64 x 44 Airfoil: GA30U-412 Wingspan: 28.4 ft Wing area: 141 sq.ft Wing chord: 5 ft Aspect ratio: 5.7 to 1 Length: 20.3 ft Height: 6.5 ft Fuel capacity: 14 gal U.S. Wheel & tire size: 600 x 6 Empty weight: 575 lbs Gross weight: 1100 lbs Span loading: 18.7 lb/ft Wing loading: 7.8 lb./sq. ft. Power loading: 16.9 lb/bhp Maneuvering speed: 85 mph Maximum level speed: 110 mph Never exceed speed: 150 mph Cruise speed: 90 mph Best glide speed: 75 mph Best rate of climb: 750 fpm Best climb rate speed: 80 mph Range: 250 sm Take off distance: 750 ft Landing distance: 500 ft
