Flight Design CTSW
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| CTSW | |
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| Type | Microlight/Ultralight |
| Manufacturer | Flight Design |
| Number built | 900+ |
| Unit cost | EU 62924.37 Base price |
The CT2K and CTSW are aircraft produced by the Flight Design company (Flightdesign Vertrieb) in Germany. The aircraft can be flown under the microlight/ultralight regulations of several countries as well as the USA FAA Light-sport Aircraft rules and the European EASA Very Light Aircraft rules. Both aircraft are high-wing designs using a 100 hp (70 kW) Rotax 912S engine in a tractor configuration (the 80 hp (60 kW) 912 is sometimes used outside of the US). The main difference between the CT2K and CTSW is the shorter wingspan of the CTSW and the redesigned wingtips. This results in higher cruise speeds for the CTSW while maintaining similar stall speeds.
Both aircraft are of composite construction, with carbon fiber being the primary material. This results in a very aerodynamic shape to the fuselage and very high useful loads (almost equal to the weight of the aircraft itself). The CTSW is so efficient that it needs to have the pitch of the propeller reduced significantly to stay within the 120-knot (222 km/h) maximum speed of the American Light-sport Aircraft (LSA) rules; in other countries, the CTSW has a higher cruising speed. In addition, the amount of negative (reflex) flaps is limited to -6 degrees in the US version; in other countries the flaps retract to -12 degrees in cruise, adding even more speed.
The CTSW is reported to be somewhat more challenging to fly than other LSA, owing to the higher wing loading and low drag; the low drag increases top speed, but requires additional planning in the descent. The control forces are light and, like most LSA, rudder coordination is necessary, owing to the close coupling of the tailplane. Flight Design increased the size of the tailplane and control surfaces for the 2006 model year, giving improved directional control at lower speeds.
Landings require proper training. The aircraft flies in a nose-down attitude with the flaps at 30 or 40 degrees, meaning that the pilot must be aggressive in the flare. However, if the stick is held back too far, the aircraft will balloon, climb, and then sink rapidly as airspeed bleeds off. The best solution appears to be to carry power into the flare when using 30 or 40 degrees flaps, and to normally land with 0 or 15 degrees flaps. In addition, the CTSW is reported to have better (less sensitive) pitch qualities in the flare with the center of gravity towards the aft end of the allowable envelope. This allows for better control of the flare, reducing the possibility of ballooning on landing. In support of this, Flight Design have changed the allowable CG range for newer production CTSWs.
Although the standard and required equipment varies by country, the CTSW is available with a Ballistic Recovery Systems parachute for the airframe. The BRS can be used to lower the entire aircraft to the ground in a controlled decent in the event of major structural failure, incapication of the pilot or engine failure over mountainous terrain.
In 2008, Flight Design announced a new model, the CTLS, which improves on the CTSW in several areas, including a revised fuel system (improved fuel venting and standard-type fuel caps), a revised tailplane and upgraded landing gear. The CTSW will stay in production alongside the CTLS for the time being.
As of February 2008, there are more than 220 CTSW registered in the USA.
[edit] Specifications (CTSW)
This aircraft article is missing some (or all) of its specifications. If you have a source, you can help Wikipedia by adding them.General characteristics
- Crew: one, pilot
- Capacity: one passenger
- Length: 6.22 m (20 ft 5 in)
- Wingspan: 8.50 m (27 ft 11 in)
- Height: 2.15 m (7 ft 1 in)
- Wing area: 9.94 m² (107 ft²)
- Empty weight: 318 kg (LSA US version) (262 kg (EU base version))
- Loaded weight: 600 kg (LSA US version) (472.5 kg (EU version with parachute))
- Max takeoff weight: 600 kg (US LSA, varies in other countries) (1320 lb (599 kg))
- Powerplant: 1× Rotax 912S 4-cylinder, 4-stroke liquid/air-cooled engine, 75 kW (100 hp)
- * Fuel capacity: 125 litres usable (33 gal)
- Baggage capacity: 50 kg (110 lb)
Performance
- Never exceed speed: 301 km/h (145 knots (US LSA))
- Maximum speed: 230 km/h (138 mph)
- Cruise speed: 112 knots (129 mph) (207 km/h) (75% at sea level) (US LSA)
- Stall speed: 65 km/h (40 mph)
- Range: 1266 km (660 nm)
- Service ceiling 4,572 m (15,000 ft)
- Rate of climb: 4.9 m/s (960 ft/min)
- Wing loading: 61 kg/m² (12.3 lb/ft²)
- Power/mass: 13.2 lb/hp (0.12 kW/kg)
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