The Sud-Est or SNCASE SE-2100, sometimes known as the Satre SE-2100 after its designer, Pierre Satre, later the chief designer of the Concorde, at the end of World War II. An all-metal tailless, pusher configuration 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.
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 aircooled 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. At different times the undercarriage legs and wheels were unfaired or faired.
The only SE-2010 built flew for the first time on 4 October 1945 at Toulouse. The test pilot was Mr. Pierre Nadot (test pilot of the S.N.C.A.S.E.-Société Nationale de Constructions Aéronautiques du Sud-Est).
The aircraft was still existed in 1952.
Engine: 1 × Renault Bengali 4Pei, 140 kW (190 hp) at 500 m (1,640 ft) and 2,400 rpm
Propeller: 2-bladed, 1.90 m (6 ft 3 in) diameter wooden
Length: 4.92 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)
Maximum speed: 226 km/h (140 mph; 122 kn)
Cruising speed: 198 km/h (123 mph; 107 kn)
Range: 500 km (311 mi; 270 nmi)
Service ceiling: 5,000 m (16,404 ft)
Wing loading: 52.83 kg/m2 (10.82 lb/sq ft)
Landing speed: 90 km/h (56 mph; 49 kn)
Crew: Two
All Aero 