PZL.55: Difference between revisions
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|span in= |
|span in= |
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|span note= |
|span note= |
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|upper span m= |
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|upper span ft= |
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|upper span in= |
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|upper span note= |
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|mid span m= |
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|mid span ft= |
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|mid span in= |
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|mid span note= |
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|lower span m= |
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|lower span ft= |
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|lower span in= |
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|lower span note= |
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|swept m=<!-- swing-wings --> |
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|swept ft=<!-- swing-wings --> |
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|swept in=<!-- swing-wings --> |
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|swept note= |
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|dia m=<!-- airships etc --> |
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|dia ft=<!-- airships etc --> |
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|dia in=<!-- airships etc --> |
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|dia note= |
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|width m=<!-- if applicable --> |
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|width ft=<!-- if applicable --> |
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|width in=<!-- if applicable --> |
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|width note= |
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|height m=2.7 |
|height m=2.7 |
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|height ft= |
|height ft= |
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|wing area sqft= |
|wing area sqft= |
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|wing area note= |
|wing area note= |
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|swept area sqm=<!-- swing-wings --> |
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|swept area sqft=<!-- swing-wings --> |
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|swept area note= |
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|volume m3=<!-- lighter-than-air --> |
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|volume ft3=<!-- lighter-than-air --> |
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|volume note= |
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|aspect ratio=<!-- sailplanes --> |
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|airfoil= |
|airfoil= |
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|empty weight kg=2300 |
|empty weight kg=2300 |
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|max takeoff weight note= |
|max takeoff weight note= |
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|fuel capacity= |
|fuel capacity= |
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|lift kg=<!-- lighter-than-air --> |
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|lift lb=<!-- lighter-than-air --> |
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|lift note= |
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|more general= |
|more general= |
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<!-- |
<!-- |
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|eng1 hp=1600 |
|eng1 hp=1600 |
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|eng1 shp=<!-- prop engines --> |
|eng1 shp=<!-- prop engines --> |
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|eng1 kn=<!-- jet/rocket engines --> |
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|eng1 lbf=<!-- jet/rocket engines --> |
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|eng1 note= |
|eng1 note= |
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|power original= |
|power original= |
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|thrust original= |
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|eng1 kn-ab=<!-- afterburners --> |
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|eng1 lbf-ab=<!-- afterburners --> |
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|eng2 number= |
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|eng2 name= |
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|eng2 type= |
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|eng2 kw=<!-- prop engines --> |
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|eng2 hp=<!-- prop engines --> |
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|eng2 shp=<!-- prop engines --> |
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|eng2 kn=<!-- jet/rocket engines --> |
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|eng2 lbf=<!-- jet/rocket engines --> |
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|eng2 note= |
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|eng2 kn-ab=<!-- afterburners --> |
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|eng2 lbf-ab=<!-- afterburners --> |
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|eng3 number= |
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|eng3 name= |
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|eng3 type= |
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|eng3 kw=<!-- prop engines --> |
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|eng3 hp=<!-- prop engines --> |
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|eng3 shp=<!-- prop engines --> |
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|eng3 kn=<!-- jet/rocket engines --> |
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|eng3 lbf=<!-- jet/rocket engines --> |
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|eng3 note= |
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|eng3 kn-ab=<!-- afterburners --> |
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|eng3 lbf-ab=<!-- afterburners --> |
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|more power= |
|more power= |
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|prop blade number=<!-- propeller aircraft --> |
|prop blade number=<!-- propeller aircraft --> |
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|prop name= |
|prop name= |
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|prop dia in=<!-- propeller aircraft --> |
|prop dia in=<!-- propeller aircraft --> |
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|prop dia note= |
|prop dia note= |
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|rot number=<!-- helicopters --> |
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|rot dia m=<!-- helicopters --> |
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|rot dia ft=<!-- helicopters --> |
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|rot dia in=<!-- helicopters --> |
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|rot area sqm=<!-- helicopters --> |
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|rot area sqft=<!-- helicopters --> |
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|rot area note= |
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<!-- |
<!-- |
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Performance |
Performance |
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|max speed kts= |
|max speed kts= |
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|max speed note= |
|max speed note= |
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|max speed mach=<!-- supersonic aircraft --> |
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|cruise speed kmh= |
|cruise speed kmh= |
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|cruise speed mph= |
|cruise speed mph= |
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|g limits=<!-- aerobatic --> |
|g limits=<!-- aerobatic --> |
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|roll rate=<!-- aerobatic --> |
|roll rate=<!-- aerobatic --> |
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|glide ratio=<!-- sailplanes --> |
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|climb rate ms= |
|climb rate ms= |
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|climb rate ftmin= |
|climb rate ftmin= |
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|climb rate note= |
|climb rate note= |
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|time to altitude= |
|time to altitude= |
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|sink rate ms=<!-- sailplanes --> |
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|sink rate ftmin=<!-- sailplanes --> |
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|sink rate note= |
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|lift to drag= |
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|wing loading kg/m2= |
|wing loading kg/m2= |
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|wing loading lb/sqft= |
|wing loading lb/sqft= |
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Latest revision as of 18:17, 26 October 2024
| PZL.55 | |
|---|---|
| |
| Schematic drawings of the PZL.55 | |
| Role | Fighter aircraft |
| National origin | Poland |
| Manufacturer | Państwowe Zakłady Lotnicze |
| Designer | Jerzy Dąbrowski |
| Status | Project |
| Primary user | Polish Air Force (planned) |
PZL.55 was a Polish pre-war project of a fighter aircraft, created at Państwowe Zakłady Lotnicze by Jerzy Dąbrowski. The design was for a single-seat low-wing all-metal monoplane. It was planned that the plane would replace obsolete fighters and lead to a significant increase in the capabilities of Polish Military Aviation.
Design and development
[edit]At the end of the 1930s, Polish Military Aviation urgently needed a modern high-performance fighter with strong armament that could put up an equal fight with the latest German designs such as the Bf 109 and Fw 190. In the summer of 1939, the PZL.55 defeated the PZL.53 and PZL.56 designs in the competition for a future fighter aircraft and completed a series of tests in the wind tunnel, giving promising results. The aviation command showed great interest in the PZL.55 project. In August 1939, the design and model of the fighter were approved and two prototypes were ordered. Due to the German-Soviet invasion in September 1939, the implementation of the PZL.55 project was stopped shortly after it had started.
The project was developed using experience with the PZL.26 sports plane and a private sports plane built by Dąbrowski for his own use. It was intended to use several very modern solutions for the Polish conditions at that time. The fighter was to have a fully retractable landing gear with air-oil shock absorbers, and powerful armament consisting of 6-8 machine guns was to be placed in the wings. The rest of the internal wing structure was to be taken up by integral fuel tanks. The wings were also equipped with flaps and automatic Handley Page slats. The wing armament was to be complemented by an autocannon firing through the propeller shaft. A retractable engine coolant radiator was placed under the fuselage, but it is possible that this rather problematic solution would be abandoned in later stages of development. The pilot's cabin was fully adapted to night flights and had heating, air conditioning and instruments for piloting without ground visibility. The plane was also equipped with a transmitting and receiving radio station, an oxygen installation and armored pilot's seat. The windshield was also to be made of thick armored glass. Some of these solutions have already been used in PZL P.24 and PZL.50.
The first prototype PZL.55/I was designed for the Hispano-Suiza 12Y49 inline engine but the final production version was to be powered by the more powerful, license-built Hispano-Suiza 12Z series engines which were still in development at the time.[1] In 1939, Hispano-Suiza provided the PZL with information that the 12Z engines were to ultimately achieve a maximum power of 1,400-1,600 hp. The approved design assumed that such power would translate into a maximum speed of 650-700 km/h, which was an unprecedented speed at that time. Ultimately, the surrender of France during World War II halted development of the 12Z engines and full-scale production did not begin until the end of the war. The Allison V-1710-23 engine was also considered, which, however, was not very realistic because deliveries from the USA would be long, expensive and prone to delays, and the Americans did not license the production of aircraft engines to other countries.
Planned specifications (PZL.55)
[edit]Data from [2]
General characteristics
- Length: 9.6 m (31 ft 6 in)
- Wingspan: 11.25 m (36 ft 11 in)
- Height: 2.7 m (8 ft 10 in)
- Wing area: 22.5 m2 (242 sq ft)
- Empty weight: 2,300 kg (5,071 lb)
- Gross weight: 3,250 kg (7,165 lb)
- Powerplant: 1 × Hispano-Suiza 12Z V-12 liquid-cooled piston engine, 1,200 kW (1,600 hp)
Performance
- Maximum speed: 660 km/h (410 mph, 360 kn)
- Range: 800 km (500 mi, 430 nmi)
Armament
- Guns: 1 x Hispano-Suiza HS.404 20 mm (0.787 in) cannon, 6-8 x 7.92 mm (0.312 in) PWU wz.36 machine guns
See also
[edit]Related development
References
[edit]Bibliography
[edit]- Glass, Andrzej. Polskie Konstrukcje Lotnicze Vol.3 (In Polish). Sandomierz, Poland: Wydawnictwo Stratus, 2008.