Junkers J 2

J 2

Third-built example of the Junkers J.2, E.252/16
Role	Fighter prototype
National origin	German Empire
Manufacturer	Junkers und Companie
First flight	11 July 1916
Introduction	1916
Retired	1916
Primary user	Luftstreitkrafte
Number built	6
Developed from	Junkers J 1

The Junkers J 2 was the first all-metal aircraft intended as a dedicated military aircraft design, the first all-metal aircraft meant to be a fighter aircraft, and was the direct descendant of the pioneering J 1 all-metal aircraft technology demonstrator design of 1915.

Background

Only some two weeks after the last known recorded flight, on 18 January 1916, of the J 1 "technology demonstrator" design of 1915, the Junkers firm had impressed Hauptmann Felix Wagenführ, head of IdFlieg' Prüfanstalt und Werft der Fliegertruppe ("Test Establishment and Workshop of the Aviation Troops") department, enough for him to contract the Junkers firm to build six all-metal monoplanes, intended as fighter prototypes. Each was to be powered by the Mercedes D.II inline engine (as the J 1 had been), and armed with one 7.92 mm (.312 in) lMG 08 Spandau synchronized machine gun. The aircraft were allocated IdFlieg serial numbers E.250/16 to E.255/16. The specification was for an aircraft that had:

a top speed of 145 km/h (90 mph)
a flight duration of 90 minutes
a climb rate to 3,000 m (9,840 ft) altitude within 20 minutes.

The contract also specified that "the greatest maneuverability and nimbleness in flight must be achieved by the aircraft", expressing a possible concern of the German governmental agency concerning the use of the heavy electrical steel sheet that made up the earlier J 1's structure. Junkers began wind tunnel and design work promptly upon receipt of the contract, and by the end of the spring of 1916 the first example was completed.

Design

The Junkers J 2's pioneering "unitized" forward fuselage structure, integrating the wing roots, engine mount and cockpit

The J 2 differed from the J 1 in having a cowling thet almost entirely enclosed the engine, a rounded upper and lower fusalage section instead of the rectangular section of the J 1., and a narrower and deeper ventral radiator enclosure, and had a horizontal stabilizer planform shape that would become familiar on later, all-duralumin Junkers monoplane designs to be built during 1917-18. The "all-moving" rudder still possessed no fixed fin, like the J 1. A faired-in headrest was provided for, as well as the possibly pioneering appearance of a "roll bar" for an open-cockpit aircraft, placed above the headrest for additional pilot protection in case of the aircraft overturning during landing. The landing gear was of the usual vee-type, but taller than that of the J 1's, and having the upper ends of the legs anchored not onto the lower longerons as on the J 1, but to the first wing rib bay beyond the wing root, with a long tailskid that emerged from the lower rear fuselage directly below the stabilizer's leading edge root. The wings had at least three different airfoil changes between root and tip, and had sections of them electrically roll-welded for stronger, more continuous bonding for greater strength. The resulting aircraft was intended to be smaller than the J 1 demonstrator, but with its steel structure, it almost equalled the J 1's completed weight.

One feature pioneered in the J 2 that would also be used in later all-metal monoplanes designed and built by Junkers in World War I, was a "unitized" forward fuselage structure, combining the engine mount, wing roots and cockpit framing into a single structure.

Operational history

The first production example of the J.2, (serial number E.250/16) was delivered to Adlershof on 2 July 1916, and started its IdFlieg-mandated static load testing. Otto Mader, one of the J 2's designers, then promised IdFlieg that the following example, E.251/16, would have even greater structural strength than that of the E.250's airframe. Leutnant Theodor Mallinckrodt, the pilot who had first "hopped" the J 1 some seven months previously, flew E.251/16 for the type's maiden flight on 11 July 1916. Mallinckrodt gave the aircraft a good overall evaluation, judging it as "very maneuverable", with good turning qualities and safe aerodynamic behavior. A short time later, IdFlieg test pilots Unteroffiziers Wendeler and Max Schade, began performing full flight evaluation tests on the six examples of the J 2 as they arrived at Adlershof .

Schade would eventually take one of the test aircraft on a flight from Berlin to Dessau later in the summer of 1916, achieving a speed of 180 km/h (112 mph) with the aircraft, which was some 16 km/h (10 mph) faster than the contemporary French Nieuport 11, but as the J 2 test aircraft still seemed to come up short in climbing performance tests when evaluated against wood structure designs like the then new Albatros D.I, the steel structure of the J 2 made it just too heavy to be able to compete in air combat over the Front.

At least one example (E.253/16) of the J 2 was fitted with slightly longer wings and matching longer ailerons, possibly in an effort to decrease the wing loading of the initial J 2 design, and at least one of the aircraft was fitted with the then-new 119 kW (160 hp) Mercedes D.III engine, achieving 200 km/h (124 mph) at full throttle.

Shortcomings of an "iron aircraft"

Despite the attempts to improve the J 2's performance and handling, by late in the summer of 1916 Hugo Junkers had come to the realization that the continued use of sheet electrical steel was no longer practical for aircraft construction, writing in his diary that:

"As a result of the first (J 1) and second (J 2) aircraft, one would ascertain that the aerodynamic efficiency was very good. We thought we [the Junkers designers] were over the hill. This, unfortunately, was not the case. We had to start again from the very beginning. The reason was that in spite of the favorable horizontal speed, the aircraft could not meet the military climb specifications...we had to develop an aircraft that not only had low drag for ease of maneuver in the horizontal plane, but that could climb well-an aircraft with a low weight to power ratio...

...This could not be achieved with iron, and we had to choose a new material...light-weight metal. But not only the choice of iron had resulted in high weight. We had built too heavy because we wanted a safe aircraft and partially because we had not extracted the optimum structural strength from the material".

Unteroffizier Schade, after making the record Berlin-Dessau flight, would later lose his life in a crash, from entering a spin on 23 September 1916 in one of the J 2s, and this event, combined with the substandard climbing performance of the J 2 series of test aircraft, caused IdFlieg to withdraw any further governmental support (effectively ending the J 2's contract) for the Junkers firm's advanced monoplane designs until a lighter metal, such as duralumin, was selected for such designs. The first attempt to use duralumin for airframe construction by the Junkers firm was the never-completed J 3 mid-wing, rotary engine-powered, aluminum tubing fuselage single-seat monoplane design, of which only the corrugated sheet duralumin-covered wing structures and "bare" tubular fuselage framing, primarily as an engineering exercise, were finished shortly before the end of 1916.

It is also thought that the contrasting promise of the advanced, low drag features of the Junkers monoplane aircraft designs, versus the Junkers firm's usage of experimental non-traditional sheet metal materials, and the firm's habit of almost constant experimentation obstructing any future hope of producing its advanced designs for the Luftstreitkräfte, compelled IdFlieg to create the Junkers-Fokker Aktiengesellschaft, abbreviated as Jfa and pronounced as if spelled "iefa" in German, on 20 October 1917,^[1] to allow Anthony Fokker, who even flew one of the J 2 aircraft in tests late in December 1916, to improve the future producibility of the advanced designs of the Junkers firm.

Operators

German Empire

Luftstreitkrafte

Specifications

General characteristics

Crew: 1
Length: 7.43 m (24 ft 4½ in)
Wingspan: 11.70 m (38 ft 4⅔ in)
Height: 3.13 m (10 ft 3¼ in)
Wing area: 19.00 m² (204.52 ft²)
Empty weight: 920 kg (2,028 lb)
Gross weight: 1,165 kg (2,568 lb)
Powerplant: 1 × Mercedes D.III water-cooled engine, 119 kW (160 hp)

Performance

Maximum speed: 200 km/h (124 mph)
Range: 615 km (382 miles)
Service ceiling: 4500 m (14,760 ft)

Armament

1 × 7.92 mm (.312 in) lMG 08/15 machine gun

References

↑ Byers, Richard (2008). "An Unhappy Marriage: The Junkers-Fokker Merger" (PDF). http://www.ufv.ca/. University of the Fraser Valley, BC, Canada. p. 12. Retrieved December 26, 2013. External link in |website= (help)

The Complete Book of Fighters. Godalming, UK: Salamander Books. p. 302.

Bibliography

Grosz, Peter and Gerard Terry. "The Way to the World's First All-Metal Fighter", AirEnthusiast Twenty-Five, 1984, Pilot Press, pp. 63–64. ISSN 0143-5450.

External links

Wikimedia Commons has media related to Junkers J 2.

Photo of second example of J 2 produced, E.251/16

World War I aircraft of the Central Powers

Fighters	AEG D.I AEG Dr.I Albatros D.I Albatros D.II Albatros D.III Albatros D.V Aviatik D.I Aviatik C.VI Daimler L.6 Euler D.I Euler D.II Fokker D.I Fokker D.II Fokker D.III Fokker D.IV Fokker D.V Fokker D.VI Fokker D.VII Fokker D.VIII Fokker Dr.I Fokker E.I Fokker E.II Fokker E.III Fokker E.IV Fokker E.V Halberstadt D.II Hannover CL.II Hannover CL.III Hannover CL.IV Hannover CL.V Hansa-Brandenburg W.12 Hansa-Brandenburg W.29 Junkers D.I Kondor D.6 Kondor E.III Naglo D.II Pfalz D.III Pfalz D.XII Pfalz Dr.I Pfalz E.I Pfalz E.II Phönix D.I LFG Roland D.II LFG Roland D.VI Siemens-Schuckert D.I Siemens-Schuckert D.II Siemens-Schuckert D.III Siemens-Schuckert D.IV Siemens-Schuckert L.I Zeppelin-Lindau D.I

Bombers and ground attack	AEG DJ.I AEG G.I AEG G.II AEG G.III AEG G.IV AEG G.V AEG J.I AEG J.II AEG R.I Friedrichshafen G.II Friedrichshafen G.III Gotha G.I Gotha G.II Gotha G.III Gotha G.IV Gotha G.V Gotha GL.VII Gotha G.IX Hannover CL.II Junkers CL.I Junkers J.I Rumpler G.I Rumpler G.II Rumpler G.III Zeppelin-Lindau Rs.II Zeppelin-Lindau Rs.III Zeppelin-Lindau Rs.IV Zeppelin-Staaken R.VI

Reconnaissance	AEG B.I AEG B.II AEG B.III AEG C.I AEG C.II AEG C.III AEG C.IV AEG C.V AEG C.VI AEG C.VII AEG C.VIII AGO C.I AGO C.II AGO C.III AGO C.IV AGO C.VII AGO C.VIII Albatros B.I Albatros B.II Albatros C.I Albatros C.III Albatros C.V Albatros C.VII Albatros C.IX Albatros C.X Albatros C.XII Aviatik B.I Aviatik B.II Aviatik C.I Aviatik C.VI DFW C.V LFG Roland C.II LVG B.I LVG C.II Rumpler C.I Rumpler C.IV Rumpler Taube

Trainers	Euler D.I

Prototypes	Albatros C.II Fokker V.1 Fokker V.2 Junkers J 1 Junkers J 2 Zeppelin-Lindau Rs.I

Junkers aircraft

Company	J 1 J 2 J 3 J 4 J 5 J 6 J 7 J 8 J 9 J 10 J 11 J 12 F 13 J 15 K 16 K 17 J 18 T 19 A 20 H 21 / J 21 / T 21 J 22 T 23 G 23 F 24 / G 24 A 25 T 26 T 27 J 28 T 29 K 30 G 31 A 32 W 33 W 34 A 35 S 36 K 37 G 38 K 39 K 47 A 48 A 50 K 51 K 53

Idflieg	CL.I D.I E.I J.I

RLM	Ju 46 Ju 49 Ju 52 Ju 60 Ju 85 Ju 86 Ju 87 Ju 88 Ju 89 Ju 90 Ju 160 Ju 187 Ju 188 Ju 248 Ju 252 Ju 268 Ju 287 Ju 288 Ju 290 Ju 322 Ju 352 Ju 388 Ju 390 Ju 488 Ju 635

"EF" (experimental)	EF 61 EF 126 EF 127 EF 128 EF 131 EF 132 EF 140 EF 150

This article is issued from Wikipedia - version of the 4/7/2016. The text is available under the Creative Commons Attribution/Share Alike but additional terms may apply for the media files.