Robin DR.200
| Robin DR.200 |
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| DR.221 Dauphin |
| Role |
Four-seat light aircraft |
| Manufacturer |
Avions Pierre Robin |
| First flight |
1964 (DR.200) |
| Number built |
348 |
| Variants |
Robin DR300 |
The Robin DR.200 is a family of French conventional landing gear single-engined light touring or training cabin monoplanes. Originally produced by Centre Est Aéronautique the company later changed its name to Avions Pierre Robin.
Development
Originally flown as the DR.200 which was a variant of the earlier DR.1050M1 with a strengthened wing and longer fuselage. The production version was the DR.250 Capitaine a four-seater with a 160 hp Lycoming O-320 engine and all-flying tailplane. The DR.250 first flew in 1965. The next development was a two-seat variant with a shorter fuselage the DR.220 2+2, it was powered by a 105 hp Continental O-200-A engine. The DR.221 Dauphin introduced a bigger 115 hp Lycoming O-235C engine. Then the DR.253 Regent was first flown in 1967, the DR.253 introduced a tricycle landing gear which was to become standard on all the following Robin designs.
Variants
- DR.200
- Prototype four-seat development of the DR.1050M1 with a Potez 105E engine, two built.[1]
- DR.220 2+2
- Shorter fuselage two-seat variant although it did have a small rear seat, powered by a 105hp Continental O-200-A engine, 83 built.[1]
- DR.221 Dauphin
- A DR.200 with four seats and powered by a 115hp Lycoming O-235C engine, 62 built.[1]
- DR.250 Capitaine
- A DR.200 with all-flying tailplane and powered by a 160hp Lycoming O-320-E engine, 100 built.[1]
- DR.250-180
- Experimental DR.250 with a 180hp Lycoming O-360-A engine, one built.[1]
- DR.253 Regent
- A DR.250 with enlarged fuselage and tricycle landing gear, powered by a Lycoming O-360-D2A engine, 100 built.[1]
Specifications (DR.221)
Data from [2]
General characteristics
- Crew: 2
- Length: 7.00 m (23 ft 0 in)
- Wingspan: 8.72 m (28 ft 7 in)
- Height: 1.85 m (6 ft 1 in)
- Wing area: 13.60 m2 (146.4 sq ft)
- Empty weight: 475 kg (1,047 lb) equipped
- Max takeoff weight: 840 kg (1,852 lb)
- Powerplant: 1 × Lycoming O-235-C2A flat-four piston engine, 86 kW (115 hp)
- Propellers: 2-bladed EVRA, 1.80 m (5 ft 11 in) diameter
Performance
- Maximum speed: 235 km/h (146 mph; 127 kn) at sea level
- Cruising speed: 220 km/h (140 mph; 120 kn) at 2,750 m (9,000 ft) (75% power)
- Stall speed: 80 km/h (50 mph; 43 kn)
- Never exceed speed: 270 km/h (170 mph; 150 kn)
- Range: 910 km (565 mi; 491 nmi)
- Service ceiling: 3,900 m (12,795 ft)
- Rate of climb: 3.3 m/s (650 ft/min)
See also
- Related development
References
Notes
- ^ a b c d e f Simpson 1991, pp. 267-270
- ^ Taylor 1969, p.66.
Bibliography
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