PZL Lala-1
| Lala-1 | |
|---|---|
|
|
| Type: | Experimental airplane |
| Design country: | |
| Manufacturer: |
PZL |
| First flight: |
April 26, 1972 |
| Number of pieces: |
1? |
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The Lala-1 was an experimental aircraft made by the Polish manufacturer PZL .
history
The Lala-1 was developed as an experimental version of the Antonov An-2 with a lattice fuselage tail for research tests for the planned TL agricultural aircraft PZL M-15 Belphegor . The abbreviation "Lala" stands for "Flying Laboratory" (Polish: Latające Laboratorium). In addition to the ASch-62 radial engine with 736 kW in the bow, an AI-25 turbine with 14.7 kN thrust was installed in the stern. After less informative soil tests, the machine should be used to test whether the spreading material can be distributed better and further with a TL drive. Previous attempts to use parts of the engine energy from fan guns to improve the spreading power were technically too complex or the available energy was too low. With jet propulsion, however, it was different, because with it, bleed air could be taken from the compressor stage of the engine for the aviochemical equipment without much effort .
The first flight took place alone with the radial engine. In the literature, this or a similar aircraft is also referred to as the Lala-2. Whether this was a second prototype or whether the Lala-1 was converted to this machine has not yet been proven. In Fliegerrevue 1/79 p. 22 the date of the first flight is February 10, 1972 and, according to internet sources, the date of the first flight with activation of the TL engine in flight is February 26, 1972.
Construction work
The aircraft is based on the An-2 and received the entire front part of the fuselage up to the rear of the wings. The air inlet for the TL engine, which was installed instead of the rear fuselage, was on the right-hand side at the height of the cockpit. The cockpit received a new entry opening on the right side, to which a permanently mounted long ladder led. The fuselage behind the wings has been completely redesigned. It tapered very quickly to the air outlet of the TL engine. The new H-tail unit was supported by a tubular steel grid construction and set significantly higher than the An-2 donor aircraft. The vertical stabilizers hung as end disks to the right and left of the horizontal stabilizer.
Technical specifications
| Parameter | Data |
|---|---|
| Copies | 1 |
| Construction year | 1972 |
| span | 18.17 m |
| length | 12.40 m |
| height | 4.00 m |
| Wing area | 71.5 m² |
| Empty mass | 4440 kg |
| Takeoff mass | 5500 kg |
| Wing loading | 27.0 kg / m² |
| crew | 2 |
| Top speed | 200 km / h |
| Cruising speed | 180 km / h |
| Tear-off speed with flaps | 60 km / h |
| Rate of climb | 7 m / s |
| Range | 440 km |
| Takeoff distance at 15 m | 270 m |
| Landing distance of 15 m | 460 m |
| Engines | ASch-62 with 736 kW and AU-25 with 14.7 kN |
literature
- Aviator Review . No. 12 , 1983, p. 577 .
- Aviator Review . No. 1 , 1979, p. 21-25 .
