SNCASE SE-2100
| SE-2100 | |
|---|---|
| |
| Role | Two seat experimental tailless pusher touring aircraft |
| National origin | France |
| Manufacturer | Sud-Est (Société nationale des constructions aéronautiques du Sud-Est or SNCASE) |
| Designer | Pierre Satre |
| First flight | 4 October 1945 |
| Number built | 1 |
The Sud-Est or SNCASE SE-2100, sometimes known as the Satre SE-2100 after its designer, was a tailless, pusher configuration touring monoplane with a single engine and cabin for two. Only one was built.
Design and development
The SE-2100 was designed by Pierre Satre,[1] later the chief designer of the Concorde, at the end of World War II. An all-metal aircraft, it had a low, cantilever, straight tapered wing with 55° of sweep on the leading edge and 10.43° of dihedral. There were fixed leading edge slots and trailing edge ailerons but no conventional flaps. The wing tips carried large, rounded fins with rudder-like rear portions which only moved outwards; they were used differentially for yaw control and jointly as flaps.[2]
The SE-2010 had a short, blunt-nosed nacelle-type fuselage with a cabin which could be configured to seat one centrally or two in side-by-side, dual control configuration. The seats were just aft of the leading edge, with a baggage compartment behind them. Access was via deep, wide, forward hinged doors on both sides; to make this possible, a piece of the wing root leading edge was an integral part of each door. A 140 hp (104 kW) Renault Bengali 4 four cylinder, inverted, inline engine was mounted in pusher configuration behind the cabin and air-cooled via a ventral scoop; it drove a two-blade propeller positioned just behind the trailing edge. The SE-2100's fixed, tricycle undercarriage had pneumatic shock absorbers and mainwheel brakes; the nosewheel was free-swivelling.[2] At different times the undercarriage legs and wheels were unfaired or faired.[1]
The SE-2010 flew for the first time on 4 October 1945.[1]
Specifications
Data from Jane's All the World's Aircraft 1948[2]
General characteristics
- Crew: Two
- Length: 4.9 m (16 ft 1 in)
- Wingspan: 9.89 m (32 ft 5 in)
- Height: 1.89 m (6 ft 2 in)
- Wing area: 15.11 m2 (162.6 sq ft)
- Airfoil: S.T. Ae.230 (Abrial-3) at root, NACA 009 at tips
- Empty weight: 518 kg (1,142 lb)
- Gross weight: 800 kg (1,764 lb)
- Fuel capacity: 144 L (31.7 Imp gal; 38.0 US gal)
- Powerplant: 1 × Renault 4Pei 4-cylinder inverted air-cooled inline engine, 140 kW (190 hp) at 500 m (1,640 ft) and 2,400 rpm
- Propellers: 2-bladed, 1.90 m (6 ft 3 in) diameter wooden
Performance
- Maximum speed: 226 km/h (140 mph, 122 kn)
- Cruise speed: 198 km/h (123 mph, 107 kn)
- Range: 500 km (310 mi, 270 nmi)
- Service ceiling: 5,000 m (16,000 ft)
- Wing loading: 52.83 kg/m2 (10.82 lb/sq ft)
- Landing speed: 90 km/h (56 mph; 49 kn)
References
