The Foo Fighter was designed and built in 1967 by Don Stewart and Tom Raybourn, Mohawk Airline pilots, and inspired by the Alcock A-1, a World War I war bird that resembles the Sopwith Pup. One distinguishing feature of the Foo Fighter is its lower wing that crosses below the fuselage, aft of the gear, and attaches on the centerline. The airframe is built from steel tubing and covered with fabric. Originally, a Falcon 200 six cylinder CID auto engine was installed, but a 130-hp Franklin Sport Four can also be used. It was first flown in 1970 with a PSRU but the engine proved to be too heavy for the power provided and the airplane was modified to use a Franklin “Sport Four” of 130 HP.
Dec 1973
This engine went out of production and so the airplane was once again redesigned to accept any of the four cylinder Lycoming engines from the O235 up to the O320 series. It is a very docile sport airplane that offers limited aerobatic capabilities.
The prototype was registered N2123.
Engine: Franklin Sport 4, 130 hp Gross Wt. 1100 lb Empty Wt. 720 lb Fuel capacity 19 USG Wingspan 20’8” Length 18’9” Top speed 145 mph Cruise 115 mph Stall 45 mph Climb rate 1200 fpm Takeoff run 450 ft Landing roll 550 ft Range 345 sm
Circa 1967, Gary L Stevenson of Spenard AK., USA, built an all-metal design based on the Wittman Tailwind. Registered N173G, it was a two-place cabin. High-wing monoplane.
The 1915 B Stevens & Sons flying boat was designed by George Armitage, and constructed by Fred Chanonhouse, production superintendent at Sturtevant Co.
1916
A two-place open cockpit, powered by a 105hp Sturtevant pusher engine, a variation appeared in 1916.
Cycle: 4 stroke No cylinders: 4 Bore: 94 mm Stroke: 84 mm Compression: 9 Displacement: 2332 cc Cooling: air Ignition: Slick magneto Dimension: 780 x 450 x 650 mm Weight: 64.5 kg Max pwr: 80 hp at 2950 rpm Fuel consumption: 220 G/hp/hr
This project was started by Steve Stephenson in Dallas, TX, USA, as a Tiger Moth replica. It uses Fisher Flying Product wings and stabilizers. The fuselage and landing gear were designed by Steve Stephenson.
This project started in the spring of 2002. Due to traveling for work for some years and building space issues for other times, the progress has been slow.
Due to scaling issues and the modernization of certain components, and a non scale engine it was decided to rename the aircraft Tigershark.
Single seat single engined high wing mono¬plane with conventional three axis control. Wing has unswept leading and trailing edges, and constant chord; flaps fitted. Cruciform tail. Pitch control by elevator on tail; yaw control by fin mounted rudder; roll control by ailerons; control inputs through stick for pitch/roll and pedals for yaw. Wing braced from below by struts; wing profile; double surface. Undercarriage has three wheels in tricycle formation. Push right go right nosewheel steering con¬nected to yaw control. Alumi¬nium tube framework, without pod. Engine mounted below wing driving pusher propeller.
In most respects the Sky Walker is a thoroughly conventional high¬wing tube and Dacron machine, powered by the Cuyuna 430. Both the aircraft and its manufacturer made their debut in 1983 and, as is becoming common with recent ultralight designs of this type, strut bracing is employed rather than the kingpost and cable bracing which has been almost universal hitherto.
Quite the most unusual feature of the Sky Walker is its use of flaps. These lift augmenta¬tion devices can be moved to four positions and at their maximum they reduce the stall speed by 3 mph (5 kph). Controls are conven¬tional three axis, with a side mounted stick controlling the elevator and differential ailer¬ons, and pedals controlling the rudder.
Price of the Sky Walker was $5495 in 1983.
Engine: Cuyuna 430, 30 hp at 6600 rpm Propeller diameter and pitch 54 x 24 inch, 1.37 x 0.61 m V belt reduction, ratio 2.1/1 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 18.0 ft, 5.49 m Height overall 9.0ft, 2.74m Wing span 32.0ft, 9.75m Constant chord 4.4 ft, 1.33 m Sweepback 0 deg Total wing area 140 sq.ft, 13.0 sq.m Wing aspect ratio 7.3/1 Empty weight 253 lb, 115kg Max take off weight 510 lb, 231kg Payload 257 lb, 117kg Max wing loading 3.64 lb/sq.ft, 17.8 kg/sq.m Max power loading 17.0 lb/hp, 7.7kg/hp Load factors; +5.0, 3.5 ultimate Max level speed 62 mph, 100 kph Never exceed speed 80 mph, 129 kph Max cruising speed 62 mph, 100 kph Economic cruising speed 50 mph, 80 kph Stalling speed 24 mph, 39 kph (with flaps) Stalling speed 21 mph, 34 kph (without flaps) Max climb rate at sea level 600 ft/min, 3.1 m/s Best glide ratio with power off 11/1
The 1936 Stephens & Fisher Scamp 36 was a single-place, open cockpit monoplane, powered by a Salmson AD-9 engine. It was registered N15893 c/n 1.
It was sold on 26 February 1940, dismantled on 11 February 1940, and sold to Fleetcraft Co (Alexandria MN), who gave it to the National Guard as a ground-school instructional airframe.
This homebuilt was designed to meet the requirements of aerobatic competition. It is stressed to + 12G and -11G. The Akro’s wing is a one-piece, all-wood structure with two spars, and its fuselage is a fabric-covered steel tube frame. Seating is for one under a sliding bubble canopy. The Model B has both a fuel and an oil system for inverted flight. The Akro is one of the most popular aerobatic ships in the monoplane class. All control surfaces are fully static-balanced.
Dec 73
The Aircraft Technologies Akro 1 first flew in March 1994.
A two seat, side-by-side, motor-glider designed by Reiner Stemme, first flown in 1986, and first produced in 1990 at the Stemme factory at Strausberg Airfield, east of Berlin. The fuselage has a central steel tube frame, which forms the attachments for the wings, undercarriage and fixed internal powerplant. The carbon fibre rear fuselage bolts onto this frame, and the cockpit sec¬tion, which is a Kevlar lined carbon fibre shell, fits on the front. It has an electrically retractable undercarriage; not the conven¬tional glider mono wheel, but the more con¬ventional powered aircraft variety (although the track is quite narrow at 1.15 m). The engine is mounted behind the cockpit with a carbon shaft running through a Kevlar tunnel to a folding prop located behind a large retracting nose cone.
There are three basic varia¬tions of the Stemme, the S10, the S10V and the S10VT. The S10 has a four cylinder 93 hp Limbach four-stroke engine powering a fixed-pitch propeller. This combination gives a cruise speed of 90 knots. The S10V uses the same engine but with a variable-pitch propeller, giving a higher cruise speed of 121 knots.
The S10VT utilises a 115 hp turbocharged Rotax 914 engine, which gives a cruise speed of 140 knots at 10,000 ft. All variations a have a 23 m wingspan and can achieve a glide ratio of 50:1 while accommodating a crew of two. The three piece, 23 metre span, folding wings, contain two 45 litre fuel tanks.
Stemme S-10VTX
The S 10 VT engine, a 115 horsepower Rotax 914 Turbo (thus the “T” in the designation) with water cooled heads and a dual ignition system, is located in the lower fuselage be¬hind the cockpit. A centrifugal clutch turns a carbon fibre driveshaft, which is encased in a Kevlar tunnel and runs through the cen¬tral console to a reduction gearbox (0.9: 1) mounted behind the propeller in the nose section. The variable pitch (the “V” in the designation) folding propeller blades extend au¬tomatically by centrifugal force when the engine is started, with the nose cone mov¬ing forward and out of the way. When the engine is stopped, the blades fold inwards by a spring system and the nose cone is re¬tracted (which takes about six seconds) and the machine becomes a glider. The two-seater has carbon-fiber wings and solar panels for 30W of electrical power once airborne.
No. Built: 60
The U.S. Air Force Academy operates 2 S 10’s as the TG-11 A model (S 10VT), 94-1400 and 94-1500 also as civil N94FT and N94FW.
All Aero 