Oberursel

Motorenfabrik Oberursel

Motorenfabrik Oberursel A.G. was a German manufacturer of automobile, locomotive and aircraft engines situated in Oberursel (Taunus), near Frankfurt (Main), Germany. The company had its origins in 1891, when Willy Seck invented a new gasoline fuel injection system and produced a small one-cylinder stationary engine of about 4 hp, which he called the Gnom. The following year he founded Willy Seck & Co. to sell the design, which became famous around the world. The engine was improved to achieve more power, but in 1897 the shareholders refused to allow Seck to develop a Gnom-powered car and he left the company. The company was reorganized as Motorenfabrik Oberursel the next year, and by 1900 had built 2,000 engines.

The same year the company granted a license to the Seguin brothers in Lyon to produce the Gnom in France. Sold under the French name Gnome, the engine became so successful that they renamed their company to the same name. In 1908 they developed a rotary version of the basic Gnome system as the Gnome Omega aircraft engine, and from there a series of larger versions of the same basic design. The new Gnome engines were wildly successful, powering many of the early record breaking aircraft.

In 1913 Motorenfabrik Oberursel took out a license on the French Gnome engine design and the similar Le Rhône 9C. They produced both, the Gnomes as the U-series, and the Le Rhônes as the UR-series. During World War I it supplied a major 100 hp-class rotary engine that was used in a number of early-war fighter aircraft designs.

The Gnome Lambda seven-cylinder 80 hp rotary engine was also produced by the Oberursel firm as the Oberursel U.0 Umlaufmotor (the generic German term for a rotary engine) as their first-ever powerplant for German military aircraft, and was used on the initial versions of the Fokker Eindecker fighter, the Fokker E.I.

When World War I started the following year the Oberursel U.I of 100 hp, a clone of the Gnome Delta 100 hp rotary, had the best power-to-weight ratio of any German engine. It went on to power most of the early German fighters, such as the Fokker and Pfalz E-series monoplanes
.
Oberursel also built a copy of Gnome’s 14-cylinder Double Lambda two-row rotary. This 160 hp (120 kW) engine, designated U.III in Germany, was difficult to build and quickly wore out in service. It was used on the Fokker E.IV and D.III designs.

The 110 hp Oberursel UR.II, the clone of the Le Rhône 9J of the same power output, was the next major success. Fokker bought the company in 1916 in order to guarantee supplies of the UR.II. This acquisition proved advantageous because Fokker was partial to rotary powered designs, and because supplies of the Mercedes D.III engine were limited. The UR.II was used in the Fokker Dr.I and Fokker D.VI.

By 1917, the UR.II had been rendered obsolete by its relatively low power and poor performance at altitude. An 11-cylinder development, the UR.III, was not used operationally. Indeed, by 1918, rotary engines had largely fallen from favor with the Idflieg and with pilots. The lack of castor oil and the poor quality of the mineral oil substitute “Voltol” severely reduced engine life and reliability.

Nevertheless, in the summer of 1918, the UR.II was installed in the Fokker D.VIII. The light weight and aerodynamic cleanliness of the D.VIII allowed it to achieve excellent performance even with the outdated UR.II.

After the war the company was purchased in 1921 by Gasmotorenfabrik Deutz, another gasoline engine manufacturer, who moved their two-stroke diesel manufacturing to the Oberursel factories. In 1930 they merged with Humboldt-Deutz, but with only one product line. The factory was eventually closed in 1932 during the Great Depression, reopening in 1934 for small-scale production.

In 1938 the company merged Klöcknerwerke AG. From this point on they were known as the Klöckner-Humboldt-Deutz Oberursel factory, known primarily for their locomotive engines.

In 1940 during World War II all diesel research was relocated to Oberursel, where Dr. Ing. Adolf Schnürle led the development of much larger and more advanced engines for aircraft use. This led to the Klöckner-Humboldt-Deutz DZ 700 8-cylinder radial engine, the DZ 710 16-cylinder boxer engine, and the DZ 720 32-cylinder H-block made from twinned 710’s. None of these designs reached operational use by the end of the war, when the factory was occupied by US troops.

For a short period in 1946 the factories were used as a tanks and trucks repair depot by the US army.
In 1956 the factories were returned to Klöckner-Humboldt-Deutz, and from then on have been used primarily for gas turbine development and production. For the next twenty years they produced a variety of designs, typically under license from other companies. In 1980 they were renamed KHD Luftfahrttechnik GmbH.

In 1990 the company was sold to what was then BMW Rolls-Royce. The new owners decided to use the Oberursel plants to produce an entirely modern engine for the “small end” of the aviation market, and started development of the Rolls-Royce BR700 family in 1991. The engines have since gone on to power a number of aircraft including Bombardier, Gulfstream V and the Boeing 717.

The factory in Oberursel is claimed to be the oldest surviving aircraft engine factory in the world.

Engines:
Gnome designs:
Oberursel U.0
licensed Gnome 7 Lambda, 68 hp (51 kW) seven cylinder rotary.

Oberursel U.I
100 hp (75 kW), nine cylinder.

Oberursel U.II
110 hp (82 kW)

Oberursel U.III
Gnome Lambda-Lambda 14-cylinder, two-row rotary engine copy. 160 hp (120 kW).

Le Rhône designs:
Oberursel Ur.II
Le Rhone 9J 110 hp (82 kW) nine cylinder rotary.

Oberursel Ur.III
11-cylinder development of the Ur.II. 145 hp (108 kW).

Nyberg Flugan / Fly

Carl Richard Nyberg (1858-1939) was a Swedish industrialist and the inventor of a successful blowtorch. He began work on this flying test-bed in 1897, with tests and alterations to the design of Flugan (The Fly) going on until around 1910. It had a wingspan of 5 meters, and the surface area of the wings was 13 m². It was powered by a steam engine heated by four of his blowtorches, producing 10 hp at 2000 rpm. The weight of the engine was 18 kg, giving a very good power-to-weight ratio for its time. The total weight of the plane was 80 kg, so the failure to fly was more related to poor propeller and wing technology. The challenge photo was probably taken in 1903 or later, when he started testing on the ice of the Baltic at his home on Lidingö outside Stockholm, rather than tethered around a circular board track in his garden.

NWT Spruce Coupe

Fits Rotax or Kawasaki engines, and two wing lengths were available.

Top speed: 75 mph
Cruise: 60 mph
Stall: 35mph
Range: 80 sm
Rate of climb: 1200 fpm
Takeoff dist: 75 ft
Landing dist: 100 ft
Engine: Zenoah, 42 hp
HP range: 22-50
Fuel capacity: 6 USG
Empty weight: 300 lb
Gross weight: 600 lb
Height: 6 ft 3 in
Length: 16.9 ft
Wing span: 22 ft
Wing area: 88 sq.ft
Seats: 1
Landing gear: tailwheel

Nurtanio NU-85 / NU-90 Belalang

NU-90 Belalang

This aircraft is a low-wing conversion of the Piper Cub L-4J.
The prototype, designated NU-85, flew on April 17, 1958, and proved to be such an improvement over the original L-4J that the Indonesian Air Force was having all its L-4Js converted into Belalangs, with the production designation NU-90.
The programme was started in 1959 and the NU-90 became the standard primary trainer at the Air Force Flying School.

Engine: Continental C90-12F, 90 hp
Span: 31 ft l in
Length: 25 ft 3 in
Height: 6 ft 8 in
Wing area: 161.5 sq.ft
Gross weight: l,500 lb
Empty weight: l,038 lb
Max speed: 115 mph
Cruising speed: 90 mph
Max rate of climb at SL: 600 ft/min
Service ceilmg: 12,000 ft
TO run: 500 ft
Landing run: 400 ft
Range: 350 miles

Nurtanio NU-25 Kunang / NU-35 Kunang / Lipnur NU-25 Kunang / NU-35 Kunang

NU-25 Kunang

Development of the original NU-25 Kunang was started in 1957, to provide Indonesian flying clubs with an economical single-seat ultra-light trainer.
The original tapered wing, with fixed slots, was replaced by a constant-chord wing of 25 percent greater area during 1960. At the same time, the Volkswagen engine has been uprated from 25 to 35 h.p. and a cockpit canopy has been fitted. Now designated NU-35, the Kunang is of conventional wooden construction, with fabric covering.

NU-35 Kunang
Engine: Volkswagen, 35 hp
Span: 23 ft ll in
Height: 5 ft 11 in
Wing area: 102.6 sq.ft
Gross weight: 743 1b
Empty weight: 504 lb
Cruising speed: 80 mph
Max rate of climb at SL: 300 ft/min

NUD NU D.38

The Nuri Demirağ Nu.D.38 was a Turkish light civil transport, with twin engines and seating for four passengers, built in the early 1940s. Only one was constructed and flown.

Design work on the Nu.D.38 twin engine light transport began about 1938 and the aircraft was largely completed by 1941, but the first flight was delayed until 1944. Turkey remained neutral through most of World War II, only entering the war in 1945, after the first flight.

The Nu.D.38, manufactured by Nuri Demirağ in Istanbul, was a high cantilever wing aircraft. The wing, of tapered plan and all aluminium alloy stressed skin construction had a built up main spar and a secondary spar. There were pairs of split flaps inboard of the fabric covered ailerons. The fixed surfaces of the tail unit were also aluminium alloy structures with stressed metal skin. The tailplane, set at the top of the fuselage, was strut-braced from below. Control surfaces were fabric covered, with trim tabs.

The fuselage of the Nu.D.38 was an oval cross-section aluminium alloy monocoque, with stressed skin over frames and longitudinal stringers. The crew sat side by side at dual controls in a cabin with side access doors. The passenger compartment seated four, each with their own window, and was accessed through a starboard side door. There was a compartment for luggage or mail in the nose.

The Nu.D.38 was powered by two 160 hp (120 kW) Bramo Sh 14-A4 radial engines, mounted to the main wing spar on steel frames. It had a fixed, conventional undercarriage. A main shock absorber leg was attached to each of the steel engine frames, braced rearwards by a short auxiliary strut. Legs and wheels were enclosed in fairings.

The Nu.D.38 was first flown on 11 February 1944. No further aircraft were produced.

Gallery

Engines: 2 × Siemens-Halske (Bramo) Sh 14-A4, 120 kW (160 hp) each
Propellers: 2-bladed
Wingspan: 13.56 m (44 ft 6 in)
Wing area: 22.34 sq.m (240.5 sq ft)
Length: 8.30 m (27 ft 3 in)
Height: 2.20 m (7 ft 3 in)
Empty weight: 1,108 kg (2,443 lb)
Gross weight: 1,850 kg (4,079 lb)
Maximum speed: 271 km/h (168 mph; 146 kn) at sea level
Cruise speed: 250 km/h (155 mph; 135 kn)
Service ceiling: 6,650 m (21,820 ft)
Rate of climb: 3.40 m/s (669 ft/min) to 4,000m (13,120 ft)
Crew: 2
Capacity: 4 passengers

NUD NU D.36

The Nuri Demirağ Nu D.36 was a 1930s Turkish two-seat training biplane built by the Nuri Demirağ Aircraft Works in Istanbul for the Turkish military.

The Nu D.36 is an unequal-span single-bay staggered biplane with a fixed conventional landing gear with a tailskid. It was powered by a 150 hp (112 kW) Walter Gemma I nine-cylinder radial engine. It had two open tandem cockpits for the pilot and trainee.

Engine: 1 × Walter Gemma I, 110 kW (150 hp)
Propeller: 2-bladed fixed pitch wooden propeller
Wingspan: 9.74 m (31 ft 11 in)
Wing area: 21.8 sq.m (235 sq ft)
Length: 7.3 m (23 ft 11 in)
Height: 2.44 m (8 ft 0 in)
Empty weight: 650 kg (1,433 lb)
Max takeoff weight: 1,000 kg (2,205 lb)
Maximum speed: 182 km/h (113 mph; 98 kn)
Range: 500 km (311 mi; 270 nmi)
Endurance: 3 hours 30 minutes
Service ceiling: 3,350 m (10,990 ft)
Time to altitude: 500 m (1,600 ft) in 2 minutes; 1,500 m (4,900 ft) in 10 minutes
Crew: 2

NST Schwarze Aerostar Chronos 12

Aerostar Chronos 12

From the Czech Republic and designed by Norbert Schwarze, the engine is an American four stroke twin. A variety of wings can be fitted.

Aerostar Chronos 12
Empty weight: 90 kg
Wing span: 9.8 m
Wing area: 13.4 sq.m
Fuel capacity: 20 lt
Certification: Vz
Engine: NS 600, 30 hp
MAUW: 200 kg
Seats: 1
Max speed: 130 kph
Cruise speed: 90 kph
Minimum speed: 35 kph
Climb rate: 2.5 m/s
Fuel consumption: 4 lt/hr
Price (1998): 19 500 DM