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Stemme S.10 / TG-11A

stemme-s10-1


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 conventional 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 variations 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
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 behind the cockpit. A centrifugal clutch turns a carbon-fibre driveshaft, which is encased in a Kevlar tunnel and runs through the central 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 automatically 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 retracted (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).

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S10
Engine: 69 kW/ 93 bhp Limbach L2400 EB1. D
Wing span: 23m / 75.46 ft
Wing area: 18.74sq.m / 201.7sq.ft
Aspect ratio: 28.22
Airfoil: HQ-41
Empty Weight: 635kg / 1400lb
Payload: 215kg / 474lb
Gross Weight: 850kg / 1874lb
Wing Load: 45.39kg/sq.m / 9.29lb/sq.ft
Cruise: 90 kts
L/DMax: 51
MinSink: 0.56 m/s / 1.83 fps / 1.08 kt
Structure: GFRP/ CFRP/ Kevlar/ Steel tube
Seats: 2

S10V
Engine: Limbach, 93 hp
Prop: variable pitch
Wing span: 23m / 75.46 ft
Wing area: 18.74sq.m / 201.7sq.ft
Aspect ratio: 28.22
Airfoil: HQ-41
Cruise: 121 kts

S10
Engine: Rotax 914, 115 hp
Wing span: 23m / 75.46 ft
Wing area: 18.74sq.m / 201.7sq.ft
Aspect ratio: 28.22
Airfoil: HQ-41
Cruise: 140 kts

 

 


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