Pierre Satre began the SE-2300 design during World War II as a conventionally laid out, all metal, two seat, single engine cantilever monoplane, with tapered low wings having 4° of dihedral built around inverted U-section main and auxiliary spars. The wings had a centre section integral with the fuselage and two outer panels, all covered with electrically welded skin. There were plain flaps, with a maximum deflection of 40°.

The fuselage of the SE-2300 was constructed from four pre-formed panels welded together. A 140 hp (104 kW) Renault Bengali 4 four cylinder, inverted, air-cooled inline engine, fed from a fuselage tank, drove a two blade propeller. The over-wing cabin seated two side-by-side with dual controls. Behind these seats was space for a third (optional in the SE-2300 and standard in the SE-2310 variant) and baggage. There were access doors and rear view transparencies on both sides. At the rear, the tailplane was mounted at mid-fuselage and the fin and deep rudder were straight tapered except near the keel and almost triangular above the fuselage.

The first and only SE-2300 first flew on 26 October 1945 and had a fixed conventional undercarriage with oleo-pneumatic springing, faired main legs and wheels and a swivelling tailwheel. The two SE-2310s had tricycle undercarriages, the first unfaired but the second with faired legs and spats.

With a four seat version, the SE-2311 under development but unbuilt, the three seat SE-3010 was entered into a 1946 French Transport Ministry contest for a four seat tourist aircraft in February 1946. It was not successful, the award going to the Nord 1200 Norécrin and development of the SE-2300 series was abandoned. The last example remained in use until at least 1956 as a company hack.

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SE-2300
Original version
Engine: 140 kW (190 hp) Renault 4 Pei
Propeller: 2-blade, 1.90 m (6 ft 3 in) diameter wooden
Wingspan: 10.13 m (33 ft 3 in)
Wing area: 15.0 m2 (161 sq ft)
Length: 7.40 m (24 ft 3 in)
Height: 2.11 m (6 ft 11 in)
Empty weight: 685 kg (1,510 lb) equipped
Gross weight: 1,015 kg (2,238 lb)
Maximum speed: 235 km/h (146 mph; 127 kn)
Cruising speed: 212 km/h (132 mph; 114 kn)
Range: 900 km (559 mi; 486 nmi)
Service ceiling: 4,650 m (15,256 ft)
Wing loading: 67 kg/m2 (14 lb/sq ft)
Power/mass: 0.10 kW/kg (0.063 hp/lb)
Landing speed: 75 km/h (47 mph; 40 kn)
Landing distance: 300 m (985 ft) from 8 m (26 ft) with flaps down
Seats: two or three
conventional undercarriage.

SE-2310/11
Engine: 170 hp Regnier 4 L-00 LO-2
Three seats

SE-2310/111
Engine: 135 hp Regnier 4
faired undercarriage legs and wheels.
Three seat

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.

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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