Author: Terry

Stephenson Tigershark

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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.

Sterner Skywalker

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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

Stephens & Fisher Scamp 36

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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.

The registration was cancelled on 26 April 1948.

Stephens Akro / Aircraft Technologies Akro 1

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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.

Gallery

Gross Wt. 1100 lb
Empty Wt. 830 lb
Fuel capacity 21 USG
Wingspan 24’4”
Length 19’
Wing area: 98 sq.ft
Engine 180-hp Lycoming
Top 192 mph
Cruise 175 mph
Stall 54 mph
Climb rate 2100 fpm
Ceiling 22,000 ft
Takeoff run 400 ft
Landing roll 900 ft
Range 375 sm
Seats: 1

Aircraft Technologies Akro 1
Engine: Lycoming IO-360, 200 hp
HP range: 100-200
Top speed: 270 mph
Cruise: 220 mph
Stall: 58 mph
Range: 1000 sm
ROC: 3500 fpm
Service ceiling: 25,000 ft
Fuel cap: 47 USG
Empty wt: 780 lbs
MTOW: 1250 lbs
Length: 17 ft
Wing span: 20 ft
Wing area: 60 sq.ft
Seats: 1
Undercarriage: tailwheel
Ultimate load: +/- 15g
Roll rate: 360 deg./sec

Aircraft Technologies Akro 1
Engine: Lycoming IO-360, 200 hp
Wing span: 6.1 m
Wing area: 5.52 sq.m
MAUW: 567 kg
Empty weight: 354 kg
Fuel capacity: 178 lt
Max speed: 434 kph
Cruise speed: 354 kph
Minimum speed: 93 kph
Climb rate: 15 m/s
Seats: 1
Fuel consumption: 40 lt/hr
Plan price (1998): $225
Kit price (1998): $22,900

Stepanchonok Kacha

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The “Kacha” (Russian: Степанчонок “Кача”) was designed by pilot Vasili Andreyevich Stepanchonok in 1930, during his time as an instructor at the Kacha flight school in Sevastopol.

The “Kacha” was designed as a cantilever high-wing glider. The wing had a double wooden spar structure and was covered with plywood sheets up to the position of the second spar. From there the covering was made of fabric.

The wide, angular fuselage featured a duralumin nose with the rest in plywood-coated wood. The bow area featured a removable aluminum deck. At the rear of the cabin there was another one made of plywood. A towing hook with release system was installed in the first frame of the fuselage.

The landing gear consisted of a central wheel with steel sheet.

The “Kacha” glider was completed in 1930 and his main purpose was to serve as a trainer at the Kacha Higher Flight School. It was presented without great success in the VII National Sailing Competitions, held in 1930 in Koktebel .

Despite the great wing aspect ratio (18.7), the good finish and the excellent construction lines, the flight characteristics of the “Kacha” were quite poor. This was largely due to the poor selection of the TsAGI-311 wing profile, of a high relative thickness and the poor aerodynamic shape of the wide fuselage, with resistance surfaces perpendicular to the air flow.

Kacha
Wingspan: 16.20 m
Wing area: 14.00 m²
Aspect ratio: 18.7
Length: 5.55 m
Empty weight: 150 kg
Wing loading: 16.4 kg / m²
Surface of the horizontal planes: 3.16 m²
Elevator area: 1.74 m²
Rudder surface area: 0.87 m²
Accommodation: 1