Valmet L-80 Turbo-Vinha
 | This article needs additional citations for verification. (December 2007) |
| L-80 | |
|---|---|
| General information | |
| Type | Trainer |
| Manufacturer | Valmet |
| Status | cancelled |
| Number built | one L-80, two L-90 prototypes |
| History | |
| Introduction date | 1983 |
| First flight | 12 February 1985 |
| Retired | 1990 |
The Valmet L-80 TP Turbo-Vinha was a prototype for a new Finnish turboprop basic trainer aircraft. The aircraft, which carried the registration OH-VBB, first flew on 12 February 1985.[1] It was destroyed in a crash on 24 April 1985, during its 14th flight, killing the test pilot Paavo Janhunen. The aircraft was a further development of the Valmet L-70 Vinka and would eventually lead to the Valmet L-90 Redigo.
The Allison turboprop engine was used in the second aircraft, the L-80 TP Turbo-Vinha (OH-VTM) which was destroyed during an aerial display in Belgium. The third of the series (OH-VTP) got the new name Redigo or RediGo (used in sales brochures).
Specifications (L-80 TP)
[edit]Data from Valmet's Turbotrainer,[2] Jane's All the World's Aircraft 1984–85[3]
General characteristics
- Crew: 1 or 2
- Capacity: up to 3[4]
- Length: 7.88 m (25 ft 10 in)
- Wingspan: 10.25 m (33 ft 8 in)
- Height: 3.3 m (10 ft 10 in)
- Wing area: 14.00 m2 (150.7 sq ft)
- Aspect ratio: 7
- Airfoil: root: NACA NACA 63-218(mod B3); tip: NACA 63-412(mod B3)[5]
- Empty weight: 840 kg (1,852 lb) equipped
- Max takeoff weight: 1,800 kg (3,968 lb) (and Max landing weight)
- Fuel capacity: 350 L (92 US gal; 77 imp gal) / 280 kg (617 lb)
- Powerplant: 1 × Allison 250-B17D turboprop engine, 268 kW (359 hp)
- Propellers: 3-bladed Hartzell, 2.19 m (7 ft 2 in) diameter constant-speed propeller
Performance
- Maximum speed: 350 km/h (220 mph, 190 kn) at 3,000 m (9,800 ft)
- Stall speed: 110 km/h (68 mph, 59 kn) idle, flaps up
- 99 km/h (62 mph; 53 kn) idle, flaps down
- Never exceed speed: 460 km/h (290 mph, 250 kn)
- Range: 1,550 km (960 mi, 840 nmi) max fuel, no reserve
- Service ceiling: 7,500 m (24,600 ft) +
- Rate of climb: 10.49 m/s (2,065 ft/min)
- Power/mass: 0.15 kW/kg (0.091 hp/lb)
- Take-off distance to 15 m (49 ft): 345 m (1,132 ft)
- Landing distance from 15 m (49 ft): 350 m (1,150 ft)
Armament
- Hardpoints: 4 with a capacity of Maximum 600 kg (1,323 lb) ; inboard pylons 250 kg (551 lb) ; outboard pylons 150 kg (331 lb), with provisions to carry combinations of:
- Rockets: 37mm or 68 mm rocket pods
- Missiles: anti-helicopter missiles
- Bombs: 250 kg (551 lb) bombs
- Other: various machine-gun pods, flares searchlight pods
See also
[edit]Related development
References
[edit]
- ^ Taylor, John W.R., ed. (1985). Jane's All the World's Aircraft 1985-86 (76th ed.). London: Jane's Publishing Co. p. 50. ISBN 0-7106-0821-7.
- ^ Green and Swanborough 1986, p. 113.
- ^ Taylor, John W.R., ed. (1984). Jane's All the World's Aircraft 1984–85 (75th ed.). London: Jane's Publishing Co. p. 50. ISBN 0-7106-0801-2.
- ^ Green and Swanborough 1986, p. 117.
- ^ Lednicer, David. "The Incomplete Guide to Airfoil Usage". m-selig.ae.illinois.edu. Retrieved 16 April 2019.