DAR - 21
General Technical Information
The DAR-21 airplane, is a two-seat tandem aircraft, with the engines ranging from 60 to 120 HP.
The cockpit is fully enclosed, with tandem seats /one behind the other/. The door is on the right side of the fuselage giving access both to seats and cargo sector. All necessary navigation and engine control instruments are mounted on one panel. Full dual controls allow flying of the aircraft both from front and rear seat.
The wing is rectangular, with single spar construction, braced by two struts at 45 % of half-span. The flaps are set at 15° during take-off and at 30° upon landing. The arrangement of flight controls is standard. Ailerons and rudder are smoothly controlled by steel cables, while the elevator is controlled by a push-pull and torque tubes. Trimmers are mounted on the moving tail surfaces. The trimmer of the elevator is controlled by a steel-plated striker control cable. Rudder trimmer is ground adjustable.
The fuselage has square cross section. The main frame is made of square tubing and steel struts with stressed aluminium skin. The cockpit is in the situated in the front part of the fuselage and contains all controls. The engine cowling is made of composite materials.
The tail-wheel is steerable and is connected to the rudder. The engine mount is made of welded steel tubes and is has a simple, reliable construction for attaching the engine and supporting equipment.
There is one 30L fuel tank in the fuselage, but we have provided the option for additional wing tanks. A fuel pump secures the fuel flow.
When flying solo, the pilot flies from the front seat, there is no restriction upon the weight of a single pilot. The seatbelts are of standard type.
The front pilot seat is the only one to be used in solo flight!
Dimensions of the airplane
| Length | 6,35 m |
| Span | 9,42 m |
| Wing Area | 12,42 m2 |
| Height | 1,80 m |
| Length | 6,35 m |
| Cab Height | 1,35 m |
| Cab. Width | 0,68 m |
Aerodynamics*
| V - min, without flaps, solo | km/h | 60 |
| V - min, without flaps, 2 occupants | km/h | 70 |
| V - min, with flaps, solo | km/h | 50 |
| V - min, with flaps, 2 occupants | km/h | 58 |
| Vy max, solo at 100 km/h | m/s | 9 |
| Vy max, 2 occupants at 100 km/h | m/s | 6.5 |
| V - economical | km/h | 110 |
| V - cruise | km/h | 160 |
| V - max SA | km/h | 185 |
| V - maximum permissible (Vne) | km/h | 205 |
| Max. side wind upon landing | m/s | 5 |
Weight
| Maximum take-off weight | kg | 450 |
| Empty weight | kg | 250 |
| Relative construction | - | 0,55 |
| gravity (this is empty/max weight) | ||
| Payload | kg | 200 |
| Relative wing load* | Kg/i2 | 36,2 |
| Estimated overload coefficients* | - | +6 / -4 |
| Max permissible overload in flight | - | +4 / -2 |
| Relative power load* | Kg/HP | 6.9 |
