ABOUT THE AIRCRAFT

T-131 PA Jungmann

Flying legend still alive!

 

Bücker Flugzeugbau GmbH

The company was founded in October 1933 by Carl Clemens Bücker. During his stay in Sweden, Bücker met a genius, young engineer Anders Johan Andersson and decided to cooperate with him and brought him to Germany. Firstly, they were localized at Berlin-Johannistlial, but they had to move to a larger permises in Berlin-Rangsdorf in 1935. The reason for this was the success of the first aircraft of this type ever produced, which was the Bücker Bü-131 Jungmann.

The second most famous aircraft designed by them was the Bücker Bü-133 Jungmeister which made its test flight in 1935. This aircraft was very similar to Jungmann, but had only one seat and was designed for aerobatics. The third well-known aircraft from the factory was Bücker Bü-181 Bestmann, low-wing cabin plane with two seats side-by-side. These aircrafts definately influenced other designers. The Bücker company's constructions were also produced in Holland, Czechoslovakia, Japan, Spain, Sweden, Switzerland and even in Egypt.
Just as the second world war broke out, Andersson returned to Sweden where he joined Svenska Aeroplan AB better known as SAAB. During the war a branch factory was established at Wemingrode in the Harz district some 200 km south-west of Berlin where components for fighter aircrafts were produced. Although situated near Berlin, one of the main targets of the Allied-bombing offensive, the factory at Rangsdorf was not damaged.

Carl Clemens Bücker

Carl Bucker was born on February 11, 1895 in Ehrenbreitstein near Koblenz, Germany. He joined the Imperial German Navy as a cadet in 1912. He transferred to the Naval Air Service and within two months had passed his pilots qualifying examinations and was promoted to Lieutenant. For the rest of the First World War he flew seaplanes from various bases on the North Sea coast. The Treaty of Versailles signed by  Germany on June 28th 1919 ordered a drastic reduction in the size of both the Army and Navy and the complete abolition of military aviation, so in 1920 Bücker moved to Sweden where he was employed by the Swedish Navy as a technical adviser and test pilot. He set up his own company there and named it Svenska Aero AB. In 1933 he went back to Germany with his new project Bücker Flugzeugbau GmbH . In 1945 he returned to Stockholm. Later, in 1956 in West Germany he took over SAAB as a representative in West Germany and took up residence in Beuel, Küdinghoven near Bonn. Bücker died on March 3, 1976 at the age of 81. However his memory lives on through the production of his superb aircraft. As you should know. nothing flies better than a Bücker Jungmann.

 

The first aircraft produced by the Bücker Flugzeugbau GmbH was called Bücker Bü-131 Jungmann. It was ready to fly within six months after establishing the factory. The aircraft was chief designer, Anders Anderson's greatest achievement. The test flight was made on April 27, 1934 by Joachim von Köppen Bücker.

Bü-131 was a two-seat biplane with front and rear open cockpits, which were destinated for student and instructor, respectively. The fuselage and tail empennage was made of steel tubes covered with fabric. The wings on the other hand were wooden. However, like the fuselage and empennage, they were covered in fabric. The landing gear was fixed and consisted of  two main legs and a tailwheel. At the beginning, the aircraft was equipped with Hirth HM 60R (80 hp) and a two-blade wooden fixed pitch propeller. After some time the engine of choice becoame the Hirth HM 504A-2 (105 hp).

The first orders were placed by the DLV Deutscher Luftsport-Verband flying schools and the Luftwaffe selected the Bü-131 as its primary training aircraft in 1936. Moreover, Bücker started to export his biplane to foreign customers from many different countries, mainly in Europe. Production licences were granted to Switzerland, Spain, Hungary, Czechoslovakia and Japan. The Japanese Army also adopted the Bü-131 as its primary training aircraft. They were the main distributor of this type of aircraft, aside from Germany. It is thought that approximately 4.000 Jungmanns were built. Up to 2006 these aircrafts were built in Poland by a company called SSH Janusz Karasiewicz. After his death, the technical documentation was bought by Air Res Aviation LTD. Today, production of the Jungmann continues in completely new and modernized headquarters located in the south-eastern part of Poland, namely in Jasionka 12 km from Rzeszów.

 

Dimensions
   Length 6,725 m (22,06 ft)
Height 2,25 m (7,38 ft)
                    Wing Span 7,40 m (24,28 ft)
Wing Area 13,50 m2 (145,3 sq ft)

 

Weights
Empty 479 kg (1056 lb)       
Maximum T-O Weight 720 kg (1587 lb)         

 

Performance
Never Exceed Speed 273 km/h (170 mph)
Max Level Speed 192 km/h (119 mph)
Cruising Speed 170 km/h (106 mph)
Stalling Speed 83 km/h (52 mph)
T-O Run 387 m (1270 ft)
Landing Run 293 m (961 ft)
Range 475 km (295 miles)
Service Ceiling 4000 m (13124 ft)      

 

Powerplant
Engine LOM M332 AK 104 kW (140 hp)
Propeller MT-Propeller Wooden Fixed Pitch    

 

The Jungmann was originally used with:

Hirth HM 60

The Hirth HM 60 was a four-cylinder inverted air-cooled inline aircraft engine designed in 1923 and first sold in 1924. The engine was of very high quality, and its sales success contributed to Hirth's rapid pre-war expansion. It was a popular engine for light aircraft delivering 80 hp (60 kW) at 2,300 rpm. Later Hirth engines built upon the HM 60's success and provided greater power with many of the same design features.


Specifications (HM 60R2)

General characteristics
   Type 4-cylinder air-cooled inverted inline engine
Bore 102 mm (4 in)
              Stroke 110 mm (4.33 in)
                                                   Displacement 3.6 L (220 cu in)
Length 856 mm (33.7 in)
Width 391 mm (15.4 in)
Height 688 mm (27.1 in)
Dry weight 97 kg (214 lb)

 

Components
   Valvetrain 1 inlet and 1 exhaust valve per cylinder
Fuel system Carburetor
              Fuel type 74 octane
                                         Cooling system Air-cooled

 

Performance
   Power output 80 hp (60 kW) at 2,400 rpm
Compression ratio 5.8:1
                           Power-to-weight ratio 0.3 hp/lb (507 W/kg) at cruise speed



Walter Minor 4-III

The Walter Minor is a family of four, six and twelve-cylinder inverted inline air-cooled engine used on light aircraft. First produced in 1929, the Minor engines have steel cylinders, aluminum heads and overhead valves, with identical bore and stroke of 105 mm (4.1 in) and 115 mm (4.5 in), respectively. Typical power ratings varied from 105 hp to 160 hp.


Specifications (Minor 4-cylinder)

General characteristics
   Type 4-cylinder inverted inline air-cooled
Bore 105mm (4.14 in)
              Stroke 115mm (4.53 in)
                                      Displacement 4 Liter (244 cu in)
Length 1,119mm (44.09 in)
Width 440mm (17.32 in)
Height 630mm (24.80 in)
Dry weight 93kg (205 lb)

 

Components
   Valvetrain 1 inlet and 1 exhaust valve per cyclinder
Fuel system 1 claudel carburetor
              Fuel type 68 octane
                                           Cooling system Air-cooled

 

Performance
   Power output 95 hp at 2,550 rpm
Compression ratio 5.3:1
        Power-to-weight ratio 2.41lb/hp at cruise power



ENMA Tigre IV

The Elizalde Tigre IV, also known as the ENMA Tigre IV, is a Spanish four-cylinder inverted air-cooled engine designed and built by Elizalde SA shortly after the Spanish Civil War.




Specifications (Tigre IVA)

General characteristics
    Type Four-cylinder, in-line, inverted, air-cooled
Bore 120 mm (4.72 in)
              Stroke 140 mm (5.512 in)
                                                Displacement 6.3 L (386.3 cu in)
Length 1144 mm (43.89 in)
Width 400 mm (15.76 in)
Height 877 mm (34.55 in)
Dry weight 120 kg (264 lbs)

 

Components
   Valvetrain Overhead valve
Fuel system Carburettor
Cooling system Air-cooled

 

Performance
   Power output 93 kW (125 hp) at 2,200 rpm
Compression ratio 6:1
             Power-to-weight ratio 0.77 kW/kg (0.47 hp.lb)

 

Currently, it is possible to install a little more modern engines such us LOM M332 or some sort of Lycoming.

LOM M332


M332 aero engine is an internal combustion four-stroke air-cooled four-cylinder inverted inline engine with low-pressure fuel priming before inlet valves and with a disengageable supercharger. The propeller is fitted directly on the front end of the crankshaft.


Specifications

General characteristics
   Type 4-cylinder inverted air-cooled supercharged inline engine
Bore 105 mm (4.13 in)
              Stroke 115 mm (4.53 in)
                                                                              Displacement 3.98 L (247.9 cu in)
Length 1,102 mm (43.4 in)
Width 425 mm (16.7 in)
Height 628 mm (24.7in)
Dry weight 102 kg (225 lb)

 

Components
   Valvetrain two camshaft operated valves per cylinder,
sodium filled exhaust valve
Supercharger Centrifugal
Fuel system Low pressure fuel injection
Fuel type Min 72 octane unleaded or 80 octane leaded
                                                     Cooling system Air-cooled

 

Performance
                                               Power output 104 kW (140 hp) at 2,700 rpm (take-off)

 

Lycoming O-320

The Lycoming O-320 is a large family of 92 different normally aspirated, air-cooled, four-cylinder, direct-drive engines commonly used on light aircraft such as the Cessna 172 and Piper Cherokee. Different variants are rated for 150 or 160 horsepower (112 or 119 kilowatts). As implied by the engine's name, its cylinders are arranged in horizontally opposed configuration and a displacement of 320 cubic inches (5.24 L).


Specifications (O-320-A1A)

General characteristics
   Type Four-cylinder air-cooled horizontally opposed engine
Bore 5.125 in (130.18 mm)
              Stroke 3.875 in (98.43 mm)
                                                                      Displacement 319.8 cu in (5.24 l)
Dry weight 244 lb (111 kg)

 

Components
   Valvetrain Two overhead valves per cylinder
Fuel system Updraft carburetor
              Fuel type Minimum grade of 80/87 avgas
Oil system Wet sump
                               Cooling system Air-cooled

 

Performance
                  Power output 150 hp (112 kW)
Compression ratio 7:1
Power-to-weight ratio 1.63 lb/hp (0.99 kW/kg)
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