Orličan L-40
| Orličan L-40 Meta Sokol | |
|---|---|
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| Type: | Sport plane |
| Design country: | |
| Manufacturer: | |
| First flight: |
March 29, 1956 |
| Production time: |
1957-1961 |
| Number of pieces: |
109 |
The Orličan L-40 Meta Sokol is a Czechoslovak sport and touring aircraft.
development
Already during the Second World War, engineer Zdeněk Rublič began with Beneš-Mráz in Choceň with the designs for a sport airplane made entirely of wood. It appeared in 1946 as Orličan - Beneš-Mráz was renamed after the end of the war - M-1 Sokol (falcon) and became internationally known and a success in 1949 after a long-distance flight from Prague via Zurich, Athens, the Far East to Australia.
The successor was initially the all-metal XLD-40 prototype with a V-tail. It was first flown by the chief test pilot Alfons Koblizek on July 31, 1950, but revealed major weaknesses and crashed in September of the same year due to lack of fuel. The model was then redesigned and given the designation LD-40 . Among other things, it received a conventional tail unit and the characteristic landing gear, in which the tail wheel had been pulled forward to the rear edge of the wing, so that it assumed a horizontal position when rolling on the ground despite the tail design. The LD-40 had its maiden flight on March 29, 1956 and in 1957 construction began on the first ten pre-series machines, which were still equipped with 77 kW Walter-Minor-4-III engines. The production version of this last model, now called the L-40 Meta Sokol (Metall-Falke), was equipped with a more powerful 103 kW LOM M 332 engine with a compressor and controllable pitch propeller, of which around 109 were built and exported up to 1961.
The GST of the GDR acquired five L-40s in 1959 and used them as touring planes for sports officials and for competitions. The last of these Meta Sokols was decommissioned in 1984.
| The L-40 of the GST | |||
| Work number | Mark | registration | deletion |
| 150508 | DM-WCL | 04/29/1959 | 05/24/1976 |
| 150509 | DM-WCM | 05/05/1959 | 10/17/1977 |
| 150511 | DM-WCN | 05/05/1959 | 01/20/1983 |
| 150512 | DM-WCO | 05/05/1959 | 10/08/1965 |
| 105513 | DM-WCP | 05/05/1959 | 02/23/1984 |
Technical specifications
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| Parameter | Data (XLD-40) | Data (LD-40) | Data (L-40) |
|---|---|---|---|
| crew | 1 | ||
| passenger | 3 | ||
| length | 7.15 m | 7.54 m | |
| span | 10.05 m | ||
| height | 2.52 m | ||
| Wing area | 14.56 m² | ||
| Wing extension | 6.9 | ||
| Wing swept | 2 ° | ||
| V position | 6.5 ° | ||
| Wing loading | 58.3 kg / m² | 58.6 kg / m² | 64.40 kg / m² |
| Power load | 6.68 kg / m² | ||
| Empty mass | 425 kg | 510 kg | 534 kg |
| Payload | 425 kg | 340 kg | 400 kg |
| payload | 314 kg | ||
| Takeoff mass | 850 kg | 934 kg | |
| Engine | an air-cooled 4-cylinder in- line engine | ||
| Type | Walter Minor 4-III |
LOM M 332 Sc with two-bladed metal variable pitch propeller V-410 |
|
| Starting power travel power |
105 PS (77 kW) at 2500 rpm 80 PS (59 kW) at 2300 rpm |
140 PS (103 kW) at 2700 rpm 100 PS (74 kW) at 2550 rpm |
|
| Fuel consumption | 24.5 l / h | 21 l / h | |
| Top speed | 240 km / h | 230 km / h | 237 km / h near the ground |
| Cruising speed | 215 km / h | 200 | 204 km / h |
| Landing speed | 95-99 km / h | ||
| Rate of climb | 2.73 m / s | 4.5 m / s | |
| Rise time | 5.50 min at an altitude of 1000 m | ||
| Service ceiling | 5000 m | 4850 m | 5000 m |
| Range | 1000 km | 850 km | normal 1047 km maximum 1107 km |
| Take-off / landing distance over 15 m | 400 m / 525 m | ||
See also
literature
- Hans-Joachim Mau: Czechoslovak aircraft . 1st edition. Transpress, Berlin 1987, ISBN 3-344-00121-3 , p. 100/101 .
- Heinz A. F. Schmidt: Airplanes from all over the world . 3rd revised edition. Transpress, Berlin 1970, p. 14 .
- Heinz A. F. Schmidt: Travel planes . In: Aerotype . Transpress, Berlin 1968, p. 6/7 .
