The success of the Jungmann led Bucker to open a second factory where a single-seat derivative could be produced in parallel with the original two-seater. The single-seater was the Jungmeister (young champion) advanced trainer, essentially a scaled-down Jungmann. First introduced in 1935, quickly developed an international reputation for its outstanding aerobatic capabilities.
Bucker Bu-133 Jungmeister Article
The initial Bu 133A had the 101-kW (135-hp) Hirth HM 6 inline but better performance than the higher-powered Bu 131. Quantity production was undertaken for the Luftwaffe, though precise details are lacking. The Bu 133B export version was produced to the extent of some 100 aircraft by Dornier in Switzerland and CASA in Spain with the 119-kW (160-hp) Hirth HM 506 inline. The definitive version, however, was the Bu 133C with a radial engine: this had excellent agility and performance, and was used as a fighter lead-in trainer as well as for advanced flying training. This model too was built in Switzerland and Spain.
The Bu 133 was built be Construcciones Aeronauticas S.A. in Spain for the Spanish Air Force under the designation ES-1, and 47 were built in Switzerland by the former Dornier-Werke for the Swiss Air Force.
In 1968, the Aero Technik Canary in Munich, Germany, began production of the BU-133 D-1, also called the Jungmeister. Its engine is a remanufactured Siemens-Halske Sh-14A4; however, due to this engine’s limited availability and demand for more power, a new version, the BU-133F, was built by Wolf Hirth GmbH with a 220 hp Franklin engine.
The Bu-133D-1 is basically as the Bu-133C but engine, optimised for constant inverted flight, Goodyear tyres, wheels and brakes, and US instruments.
Bucker Prado Sl offered kits to build the former German Jungmann two-seat aerobatic biplane using original Bucker/CASA Bu 131 jigs, plus Jungmeister single-seat aerobatic biplane.
Bu 133A
Engine: Hirth HM 6 inline, 101-kW (135-hp)
Bu 133B
Engine: Hirth HM 506 inline, 119-kW (160-hp)
Bu 133C Jungmeister
Engine: l x Siemens Sh 14A-4, 119kW (160hp)
Span: 6.6m (21 ft 7.75in)
Length: 6m (l9ft 8.25 in)
Empty weight: 420 kg / 925 lb
Max T/O weight: 585 kg (1,290 lb)
Max speed: 134 mph / 116 kt / 215 kph at sea level
Max cruise: 108 kt / 124 mph / 200 kph
Climb to 3300 ft / 1000m: 2 min 50 sec
Service ceiling: 19,685 ft / 6000 m
Operational range: 311 mi / 269 nm / 500 km
Optional fuel: 8.6 ImpGal / 39 lt
Bu 133 D-1
Engine: Siemens Sh-14A-4 Bramo, 158 hp
Length: 19.751 ft / 6.02 m
Height: 7.71 ft / 2.35 m
Wingspan: 21.654 ft / 6.6 m
Wing area: 129.168 sq.ft / 12.0 sq.m
Max take off weight: 1411.2 lb / 640.0 kg
Weight empty: 992.3 lb / 450.0 kg
Max. weight carried: 419.0 lb / 190.0 kg
Max. speed: 113 kts / 210 km/h
Initial climb rate: 1082.68 ft/min / 5.5 m/s
Service ceiling: 12467 ft / 3800 m
Wing load: 10.87 lb/sq.ft / 53.00 kg/sq.m
Range: 205 nm / 380 km
Endurance: 2 h
Crew: 1
All Aero 