Ikarus C42
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| C42 | |
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| Type | Fixed wing microlight aircraft |
| Manufacturer | Comco Ikarus GmbH |
| Designed by | Hans Gygax |
| Maiden flight | 1996 |
| Number built | 650+ |
| Unit cost | approx €45000 |
The Ikarus C42 is a German two-seat, fixed tricycle gear, general aviation microlight airplane, used primarily for flight training, touring, and personal flying.
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[edit] Design and development
The Ikarus C42 is a single-engined high-wing monoplane with side-by-side seats for two in a 1.22m wide cabin. The C42 is manufactured with either a 80 hp Rotax 912 engine or the 100 hp Rotax 912s engine. The Rotax engine has low fuel consumption and low noise. The engine drives a gearbox of 2.273:1 reduction ratio which then drives the propeller. This typically means the engine running at a full power shaft speed of 5800rpm will turn the propeller at 2550rpm.
The aircraft is structurally supported by a 'backbone' of large diameter aluminum tube running the length of the aircraft. The cabin and fuselage shell is a composite material and, being non-structure, can be removed for inspection and repair.
The wings are constructed of tubular front and rear spars. The wings and flying control surfaces are covered in Kevlar/Mylar/Polyester laminate. The wings can be removed or folded (if optional folding kit is installed) for storage and transportation. The wing-tips are of composite construction which reduce drag and improve low speed handling. Access to the cabin is provided by 2 Gull-wing doors.
[edit] Controls
A single stick positioned centrally in the cabin controls the ailerons and elevators. Electrical pitch trim is controlled by 2 buttons on the top of the stick operated by the thumb. A push to talk button is on the front of the stick operated by the index finger. Also on this stick is a vertical hand operated brake lever similar to a motorbike's front brake lever.
Rudder pedals are dual control. Due to the nonadjustable seats the distance from the seat to the pedals is fixed.
The flaps are controlled by a centrally mounted lever on the roof of the cabin. The relatively short lever does make the operation of lowering flaps quite physical when combined with holding the centre control stick at the same time.
[edit] Specifications (Ikarus C42 [with Rotax 912s])
[edit] V speeds
Where a single speed appears, it is applicable to the aircraft at maximum gross weight (1040 lb/473kg). Where a range appears, the lower speed is applicable at empty weight (572lb/260kg)and the higher speed is applicable at maximum gross weight.
- VR (rotation): 40 kias (74 km/h)
- VY (best rate of climb): 62 kias (115 km/h)
- VA (maneuvering): 82 kias (152 km/h)
- VNO (max cruise): 105 kias (194 km/h)
- VNE (never exceed): 121 kias (224 km/h)
- VFE (flaps extended): 63 kias (117 km/h)
- VREF (40° flaps, approach): 52 - 60 kias (96 - 111 km/h)
- VS0 (stall, dirty): 33 kias (61 km/h)
- VS1 (stall, clean): 42 kias (78 km/h)
General characteristics
- Crew: 1
- Capacity: 1 passenger
- Length: 20 ft 6 in (6.25 m)
- Wingspan: 31 ft 0 in (9.45 m)
- Height: 7 ft 4 in (2.24 m)
- Wing area: 134.5 ft² (12.5 m²)
- Empty weight: 583 lb (265 kg)
- Max takeoff weight: (depends on country) approx 1,041 lb (473 kg)
- Powerplant: 1× Rotax 912s flat-4 engine, 110hp (75 kW) three-blade, ground adjusted, carbon fibre, fixed-pitch propeller
Performance
- Range: 432 mi (375 nm, 695 km)
- Extended range 898 mi (780 nm, 1,445 km) with long-range tanks
- Rate of climb: 1050 ft/min (320 m/s)
[edit] External links
[edit] See also
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