In Zürich, Switzerland, Friedrich Hansen built in 1909 the Monoplan III monoplane which crashed after some trials.
Hansen Monoplan III
Monoplane
Hansa-Brandenburg W.34
Continuing the line of two-seat patrol fighter monoplanes initiated with the W.29, the W.34 was the final WWI development of the series of float seaplanes designed for the Hansa- und Brandenburgische Flugzeug- Werke by Ernst Heinkel and Hans Klemm. Essentially a scaled-up W.33 intended for the 300hp Basse und Selve BuS IVa six-cylinder water-cooled engine, only one prototype of the W.34 had been completed by the end of the War. Additional examples powered by the 300hp Fiat A 12bis engine were built after the termination of hostilities.
Max take-off weight: 2270 kg / 5005 lb
Empty weight: 1534 kg / 3382 lb
Wingspan: 16.60 m / 54 ft 6 in
Length: 11.10 m / 36 ft 5 in
Wing area: 49.0 sq.m / 527.43 sq ft
Max. speed: 175 km/h / 109 mph
Hansa-Brandenburg W.33 / Kjeller FF.8 Make
Ordered in April 1918, the W.33 was basically a larger and more powerful development of the W.29 and, augmenting the smaller fighter seaplane, saw service from North Sea air stations during the closing months of World War I.
The W.33 was powered by a 260hp Mb IVa six-cylinder inline water-cooled engine and armament normally comprised two forward-firing 7.62mm LMG 08/15 machine guns and one Parabellum in the rear cockpit. One aircraft was experimentally fitted with a 20mm Becker cannon in the rear cockpit, and several aircraft were fitted with radio and had one of the LMGs removed.
At least six of an initial order of 26 W.33s had been taken into the German Navy’s inventory when hostilities terminated, but the Norwegian Naval Flying Boat Factory built 30 under licence and the Norwegian Army Aircraft Factory built a further 11.
Kjeller Aircraft Factory license built Hansa-Brandenburg W.33 as the F.F.8 Måke (Seagull).
The Finnish Aviation Force’s Aircraft Factory assembled two W.33s as pattern aircraft in 1922, and licence-manufactured a further 120 during 1923-26. Two were sold to Latvia. Finnish manufactured planes were powered by 300 hp Fiat A-12bis motors.
W.33
Engine: 1 x 183kW Maybach Mb.IV
Wingspan: 15.85 m (52 ft)
Length: 11.10 m (36 ft 5 in)
Height: 3.37 m / 11 ft 1 in
Wing area: 44.0 sq.m / 473.61 sq ft
Max take off weight: 2050 kg (4510 lb)
Empty weight: 1420 kg / 3131 lb
Maxi¬mum speed: 173 km/h (107 mph)
Ceiling: 5000 m / 16400 ft
Armament: 2-3 x 7.92mm machine guns
Crew: 2
Hansa-Brandenburg W.29
Evolved from the W.12 two-seat patrol fighter biplane in parallel with the W.27, the W.29 was essentially a monoplane derivative powered, in prototype form, by the 195hp Benz Bz IIIbo eight-cylinder Vee engine. The span and chord of the monoplane wing approximated in area to the biplane wings of the W.12, and the wing itself was a two-spar wooden structure with fabric skinning. The 150hp Benz Bz III six-cylinder inline water-cooled engine was standardised for the production model of the W.29, which began operations with the German Navy in April 1918. Over 150 W.29s are known to have been delivered to that service in two basic versions, one equipped with radio and fitted with a single synchronised 7.92mm LMG 08/15 machine gun plus a Parabellum on a flexible mount in the rear cockpit, and the other having two forward-firing LMGs and lacking radio equipment. The W.29, operating from Zeebrugge, Borkum and Norderney, achieved considerable operational success during the closing stages of World War I. In 1921, licence production of the W.29 was initiated by the Danish naval dockyard, 15 being built and these continuing in Danish Navy service until 1931.
W.29
Engine: 1 x 112kW Benz Bz III
Span: 13.50 m (44 ft 3.5 in)
Length: 9.35 m (30 ft 8.5 in)
Wing area: 32.2 sq.m / 346.60 sq ft
Max take-off weight: 1494 kg / 3294 lb
Empty weight: 1000 kg / 2205 lb
Maximum speed: 176 km/h (109 mph)
Crew: 2
Armament: 2-3 x 7.92mm machine guns
Hanriot H.232
The H.230.01, service serial H.790, flew for the first time in June 1937. It was an advanced two-seat trainer which had a general resemblance to the H.220 but was of much lighter construction. Power was provided by two 127kW Salmson 6AF-00 engines and its configuration included a short crew canopy faired into the upper decking of the rear fuselage and a conventional . strut-braced tail unit, and the fixed main landing gear units incorporated spatted wheel fairings. During further tests it was decided to introduce considerable dihedral at the wingtips to improve stability, but the H.231.01 which followed in May 1938 had dihedral increased over the whole wing span, and the unusual wingtip arrangement of the modified H.230 was eliminated. Twin fins and rudders were introduced and power increased with 172kW Salmson 6AF engines. The Hanriot H.232.01 reverted to a single fin and rudder and had 164kW Renault 6 Q-o engines plus retractable landing gear. The H.232.02, first flown in August 1938, introduced a redesigned cockpit; it was tested officially between October 1938 and May 1939. The type was then given a twin fin and rudder tail assembly and was flown in this new configuration in December 1939, then redesignated H.232/2.01.
An order for 40 aircraft had already been received from the French air ministry, and this was increased to 57 examples shortly afterwards. By then known as the NC.232/2, they incorporated minor improvements including redesigned rudders and engine cowlings. Full navigational equipment was installed. Three reached Finland. Two were from Germany, and these were not taken into service until the Winter War 1939-40 with the Soviet Union was over. Deliveries to the Armee de I’Air started in February 1940, 35 being taken on charge up to the June 1940 Armistice. The NC.232/2s were,used by the training sections attached to the 51th and 54th Escadres, which were equipped with Breguet 691and 693 attack bombers. Twenty aircraft found on airfields when the German forces occupied Vichy, France, in 1942 were reduced to scrap.
Hanriot H.220
Included among exhibits at the Salon de l’Aeronautique held in Paris in November 1936 was a striking all-metal twin-engined three-seat fighter. It had a somewhat abbreviated oval-section monocoque fuselage, a shoulder-mounted semi-cantilever wing carrying split trailing-edge flaps over its entire span and two 450hp Renault 12Roi 12-cylinder inline air-cooled engines projecting ahead of the fuselage nose. This, the H.220, had been designed to a C3 requirement prepared by the Service Technique de l’Aeronautique and issued in October 1934. Other contenders were the Breguet 690, the Potez 630, the Loire-Nieuport 20 and the Romano 110. As it became evident that the H.220 would be underpowered, the Renault engines were discarded in favour of 680hp Gnome-Rhone 14M 14-cylinder radials, and, with these installed, the first flight test was made at Avord on 21 September 1937.
The intended armament of the H.220 comprised two forward-firing 20mm cannon and two aft-firing 7.5mm MAC 1934 machine guns on a flexible mounting, but, in the event, no armament was fitted. On 17 February 1938, the prototype made a forced landing at Avord after losing the starboard propeller following a failure in the reduction gearbox. The poor stability evinced during flight testing of the H.220 (which had resulted in progressive changes in the contours and size of the vertical surfaces), coupled with inadequate internal capacity and some lack of sturdiness revealed by the forced landing (as a result of which the fuselage was irreparable), dictated major redesign, resulting in the H.220-2.
After the partial destruction of the H.220, major redesign was initiated by the Societe Nationale de Constructions Aeronautiques du Centre, or SNCA du Centre, which had absorbed the Hanriot facility at Bourges on 1 February 1937. The oval-section monocoque fuselage of the original H.220 was discarded in favour of a fuselage built as two half shells mated by a central keel. An entirely new tail assembly with twin endplate vertical surfaces was fitted and the Gnome-Rhone 14M radial engines were enclosed by low-drag nacelles. These features were mated with the wing of the original H.220 to result in the H.220-2, which was first flown (as the H.220 No 02) on 17 March 1939. Four months later, in July 1939, this prototype was to be displayed statically as the NC 600 No 01 multi-seat fighter at the Salon de l’Aeronautique. In fact, the genuine NC 600 was to differ from the H.220-2 in several major respects.
H.220
Max take-off weight: 3700 kg / 8157 lb
Empty weight: 2673 kg / 5893 lb
Wingspan: 12.80 m / 41 ft 12 in
Length: 7.87 m / 25 ft 10 in
Height: 3.40 m / 11 ft 2 in
Wing area: 21.16 sq.m / 227.76 sq ft
Max. speed: 520 km/h / 323 mph
Range: 850 km / 528 miles
H.220-2
Max take-off weight: 3850 kg / 8488 lb
Empty weight: 2820 kg / 6217 lb
Wingspan: 12.80 m / 41 ft 12 in
Length: 7.87 m / 25 ft 10 in
Height: 3.40 m / 11 ft 2 in
Wing area: 21.16 sq.m / 227.76 sq ft
Max. speed: 532 km/h / 331 mph
Range: 770 km / 478 miles
Hanriot H.170 / H.171 / H.172 / H.173 / H.174 / H.175 / H.180 / H.181 / H.182 / H183 / H.184 / H.185 / H.190 / H.191 / H.192 / H.195
The Hanriot H.170, H.180, and H.190 were a family of light utility aircraft designed by Montlaur and produced in France in the 1930s. First flown in 1934 and all introduced in 1934, they appeared side-by-side at the Paris Air Show that year, the model numbers distinguishing between versions powered by Salmson, Renault, and Régnier engines respectively.
In basic construction, the different variants were otherwise almost identical, as largely conventional monoplanes with high, strut-braced wings and fixed, tailskid undercarriage. The pilot and one or two passengers sat in an extensively-glazed, enclosed cabin.
Although usually described as a monoplane, this family of aircraft all featured small, stub wings at the bottom of the fuselage. These carried the fuel tanks and served as a mounting point for the wing struts and undercarriage. An interesting feature was that the upper portion of the rear fuselage was a removable module, allowing it to be replaced with alternative modules for different roles, for example to carry a stretcher, or a second, open cockpit for pilot or gunnery training.
The H.182 was the major production version, accounting for 346 out of the total of 392 aircraft built. Most of these were produced as part of a government order for machines to equip the Cercles Aériens Régionaux reserve flying units, with 172 aircraft still operational at the Fall of France in 1940.
Ten more were purchased by the Second Spanish Republic for use in the Spanish Civil War, and 50 aircraft originally ordered by the French government were diverted to Turkey as part of a military aid agreement.
Variants:
H.170 – two-seat military observation version with Salmson 6Te engine (1 built)
H.171 – three-seat civil tourer version of H.170 (1 built)
H.172
H.172B – two-seat trainer (1 built)
H.172N – three-seat tourer (7 built)
H.173 – aerobatic trainer version (1 built)
H.174 – three-seat trainer (1 built)
H.175 – liaison aircraft for French Navy (10 built)
H.180
H.180T – three-seat tourer with Renault 4Pdi engine (1 built)
H.180M – two-seat military observation version with Renault 4Pei engine (1 built)
H.181 – air ambulance version of H.180T (1 built)
H.182 – main production version as trainer aircraft for French reserve aviation units.
H.183 – aerobatic trainer with Renault 438 engine (1 built)
H.184 – trainer version with uprated version of Renault 4Pei engine (1 built)
H.185 – two-seat liaison version for French navy (6 built)
H.190
H.190M – two-seat observation aircraft with Régnier 60-01 engine (1 built)
H.191 – three-seat tourer (1 built)
H.192
H.192B – two-seat trainer (1 built)
H.192N – two-seat civil trainer with Régnier 6Bo.1 engine (9 built)
H.195 – two-seat liaison aircraft with Régnier 6Bo.1 engine (1 built)
Operators:
French Air Force
French Navy
Spanish Republican Air Force
Turkish Air Force
Specifications:
H.182
Engine: 1 × Renault 4Pei, 104 kW (140 hp)
Wingspan: 12.00 m (39 ft 5 in)
Length: 7.22 m (23 ft 8 in)
Height: 3.15 m (10 ft 4 in)
Wing area: 19.0 m2 (204 ft2)
Empty weight: 604 kg (1,331 lb)
Gross weight: 887 kg (1,955 lb)
Maximum speed: 190 km/h (120 mph)
Range: 600 km (370 miles)
Service ceiling: 5,500 m (18,400 ft)
Crew: Two, pilot and instructor
Hanriot H.115
After its return to Hanriot’s Bourges factory, the H.110 was fitted with a redesigned fuselage nacelle and an uprated Hispano-Suiza 12Xbrs engine offering 690hp. A 33mm APX cannon was mounted in a bulged housing beneath the central nacelle and a four-bladed propeller supplanted the three-blader. With these modifications, the fighter re-emerged as the H.115 and was flown for the first time in April 1934. Further modifications were undertaken by the factory from November 1934, and, in June 1935, the H.115 was submitted to Villacoublay for official evaluation. Flight testing ended on 16 August. At this time it was concluded that, in view of its radical configuration, the H.115 was of no more than academic interest.
Max take-off weight: 1786 kg / 3937 lb
Empty weight: 1428 kg / 3148 lb
Wingspan: 13.50 m / 44 ft 3 in
Length: 7.60 m / 24 ft 11 in
Height: 2.69 m / 8 ft 10 in
Wing area: 24.00 sq.m / 258.33 sq ft
Max. speed: 390 km/h / 242 mph
Hanriot H.110
Debuting in April 1933, the H.110 fighter was designed by Jean Biche. It was a contender in the C1 competition promoted initially by the Service Technique de l’Aeronautique in 1930 and upgraded in January 1931 by a supplement to the specification. The H.110 was a single-seat fighter in which the pilot and engine occupied a central nacelle, and twin parallel booms attached to the extremities of the wing centre section carried the tail assembly. Of all-metal construction, the H.110 was powered by a 500hp Hispano-Suiza 12Xbrs geared and supercharged liquid-cooled engine driving a three-bladed pusher propeller. A ring-type radiator was mounted in the nose of the nacelle and embodied an adjustable cone to regulate the airflow. Largest and heaviest of the contending fighters, the H.110, which carried an armament of two fixed 7.5mm MAC machine guns, proved slower and less manoeuvrable than most of its competitors. In March 1934, it was returned to the Bourges factory for modifications, re-emerging as the H.115.
Max take-off weight: 1750 kg / 3858 lb
Empty weight: 1260 kg / 2778 lb
Wingspan: 13.50 m / 44 ft 3 in
Length: 7.96 m / 26 ft 1 in
Height: 2.70 m / 8 ft 10 in
Wing area: 24.00 sq.m / 258.33 sq ft
Max. speed: 355 km/h / 221 mph
Range: 600 km / 373 miles
Hanriot-Gnome Militaire
Hanriot’s entry into the 2nd Military Trials in 1912 was smaller than the X or XI. The fuselage appears to be all-wood, and the undercarriage is reduced to four legs. The pylon is a pyramid similar to a Nieuport or Morane-Borel, and a high metal cowling encloses the Gnome engine. This would seem to the last of the early-style Hanriots.
All Aero 