Junkers J.1000

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Junkers J. 1000
Type: Airliner
Design country:

German EmpireGerman Empire German Empire


Junkers aircraft works

Production time:

Project draft

The Junkers J 1000 was a design by Junkers Flugzeugwerke for a large airliner in duck design from the 1920s.


The project draft was presented to the public in 1924 on the occasion of the 63rd general meeting of the VDI in Hanover . The J 1000 should be able to transport 100 passengers and 10 crew members during a flight time of 10 hours. The design represented the consistent implementation of Junkers' ideas for the use of “thick” load-bearing wings , which he stated in his flying wing patenthad already worked out in 1910. In addition to the passenger, luggage and crew compartments, fuel and engines should also be housed in the thick, cantilevered wing. Also noteworthy is the landing gear, which was to be drawn into the two forward-facing tail girders and covered by a blind at the bottom. The underside of these girders was reinforced by a runner so that they could land with the landing gear retracted in an emergency landing.

The plans for the engine system contained novel approaches; Free piston compressors were to be used for the first time in aircraft construction . Turbines located behind the propellers should be powered by compressed air generated by the compressors. This system was designed for an output of four times 1000 hp. At a later revision date, however, the use of four conventional diesel engines instead of the turbines directly in front of the leading edge of the wing was planned.


As a tubular frame with corrugated sheet metal. The passenger compartments were located at the thickest part of the wing (2.30 m high). Twelve cabins with six people each in the front part and 14 cabins for two people each in the center aisle of the wing were planned.
Two tail girders that were constructed like the structure and connected the structure to the front wing. In addition to the landing gear shaft for the main landing gear, there should be dining and viewing rooms for 18 people each.
Tail unit
The front wing (horizontal stabilizer) was designed as a pendulum rudder. The two vertical stabilizers were in the extension of the stabilizer girders. In addition, there were two rudderless fin near the wing tips.

Technical specifications

Parameter Data
crew 10
Passengers 100
length 24 m
span 80 m
greatest wing chord 10 m
largest wing height 2.30 m
greatest height 7.50 m
Wing area 600 m²
payload 12,000 kg
Max. Takeoff mass 36,000 kg
Top speed 190 km / h
Engines 4 × 1000 PS free piston compressors or 4 × 2000 PS diesel engines

See also


  • Karl R. Pawlas: Der "Zukunftseindecker" , Aviation Lexicon, Article ID: 2060-100-3

Web links