sunnuntai 20. toukokuuta 2018

Hawker Tornado

The Hawker Tornado was a British single-seat fighter aircraft design of World War II for the Royal Air Force as a replacement for the Hawker Hurricane. The planned production of Tornados was cancelled after the engine it was designed to use, the Rolls-Royce Vulture, proved unreliable in service. A parallel airframe with the Napier Sabre continued into production as the Hawker Typhoon.

Shortly after the Hawker Hurricane entered service, Hawker began work on its eventual successor. Two alternative projects were undertaken: the Type N (for Napier), with a Napier Sabre engine, and the Type R (for Rolls-Royce), equipped with a Rolls-Royce Vulture powerplant. Hawker presented an early draft of their ideas to the Air Ministry who advised them that a specification was in the offing for such a fighter. 
                 Hawker Tornado (with Rolls-Royce Vulture engine).jpg
                               Hawker Tornado (P5224)

                Kuvahaun tulos haulle Hawker Tornado
                                Hawker Tornado N (HG641)

                 Kuvahaun tulos haulle Hawker Tornado

The specification was released by the Ministry as Specification F.18/37 after further prompting from Hawker. the specification called for a single-seat fighter armed with twelve 7.7 mm machine guns, a maximum speed of 644 km/h at 4,600 m and a service ceiling of 10,700 m were required. Two prototypes of both the Type N and R were ordered on 3 March 1938.

Both prototypes were very similar to the Hurricane in general appearance, and shared some of its construction techniques. The front fuselage used the same swaged and bolted duralumin tube structure, which had been developed by Sydney Camm and Fred Sigrist in 1925. The new design featured automobile-like side-opening doors for entry, and used a large 12 m wing that was much thicker in cross-section than those on aircraft like the Spitfire. The rear fuselage, from behind the cockpit, differed from that of the Hurricane in that it was a duralumin, semi-monocoque, flush-riveted structure. 

The all-metal wings incorporated the legs and wheel-bays of the wide-track, inward-retracting main undercarriage. The two models were also very similar to each other; the R plane had a rounder nose profile and a ventral radiator, whereas the N had a flatter deck and a chin-mounted radiator. The fuselage of the Tornado ahead of the wings was 30 cm longer than that of the Typhoon, the wings were fitted 76 mm lower on the fuselage, and the radiator was located beneath the fuselage. The X-24 cylinder configuration of the Vulture required two sets of ejector exhaust stacks on each side of the cowling, and that the engine was mounted further forward than the Sabre in order to clear the front wing spar.
                Kuvahaun tulos haulle Hawker Tornado
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General characteristics
Crew: One, pilot
Length: 10.01 m
Wingspan: 12.78 m
Height: 4.47 m
Wing area: 26.3 m²
Empty weight: 3,800 kg
Useful load: 1,039 kg
Loaded weight: 4,318 kg for P5219
Max. takeoff weight: 4,839 kg
Fuel capacity: 636 Litres
Powerplant: 1 × Rolls-Royce Vulture II or X-24 piston engine, 1,760 hp 1,312 kw Vulture II, Vulture V: 1,980 hp 1,476 kw
Propellers: 3 or 4 bladed propeller
Propeller diameter: 338 cm, Vulture: 306cm
Maximum speed: 641 km/h for Vulture V at 7,102 m.
Service ceiling: 10,640 m
Wing loading: max takeoff: 184.81 kg/m²
Power/mass: max takeoff 3.58 kg/Kw
Time to height: 7.2 min to 6,100 m
Guns: Provision for 12 × 7.7 mm Browning machine guns (1st prototype P5219) 
or 4 × 20 mm Hispano cannon. (2nd and Centaurus prototypes P5224, HG641).

                
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                Kuvahaun tulos haulle Hawker Tornado


                Kuvahaun tulos haulle Hawker Tornado

                Kuvahaun tulos haulle Hawker Tornado
On 6 October 1939, the first prototype (P5219) was flown by P.G. Lucas, having first been moved from Kingston to Langley for completion. Further flight trials revealed airflow problems around the radiator, which was subsequently relocated to a chin position. Later changes included increased rudder area, and the upgrading of the powerplant to the Vulture Mark V engine. Hawker production lines focused on the Hurricane, with the result that completion of the second prototype (P5224) was significantly delayed. It featured the chin radiator, additional window panels in the fairing behind the cockpit, and the 12 x 7,7 mm machine guns were replaced by four 20 mm Hispano cannon. It was first flown on 5 December 1940, and was powered by a Vulture II, although as in the case of the first prototype, a Vulture V was later installed.

In order to avoid upsetting the Hurricane lines, production was sub-contracted to Avro (another company in the Hawker group) in Manchester and Cunliffe-Owen Aircraft in Eastleigh, with orders for 1,760 and 200 respectively being placed in 1939. However, only one of these aircraft, from Avro, was ever built and flown, this being R7936. Shortly after its first flight at Woodford, on 29 August 1941, the Vulture programme was abandoned, followed closely by the cancellation of the Tornado order. At that time four aircraft were at various stages of production at the Avro plant at Yeadon, West Yorkshire.


The Vulture was effectively cancelled by Rolls-Royce in July 1941, partly due to the problems experienced in its use on the Avro Manchester, but mostly to free up resources for Merlin development and production. The Rolls-Royce Merlin was also starting to deliver the same power levels. However, the Vulture engine installation in the Tornado was relatively trouble free and the aircraft itself had fewer problems in flight than its Sabre-engined counterpart. The third prototype (HG641), the only other Tornado to fly, was flown on 23 October 1941, powered by a Bristol Centaurus CE.4S sleeve valve radial engine. This Tornado was built from two incomplete production airframes (R7937 and R7938), was a testbed for a number of Centaurus engine/propeller combinations and was the progenitor of the Hawker Tempest II.

maanantai 14. toukokuuta 2018

Caproni Vizzola F.5

The Caproni Vizzola F.5 was an Italian fighter aircraft built by Caproni. It was a single-seat, low-wing cantilever monoplane with retractable landing gear.

The F.5 was developed in parallel with the Caproni Vizzola F.4, with which it shared a common airframe. Design began in late 1937 by a team led by F. Fabrizi. The aircraft had a welded steel-tube fuselage and wooden wings; the fuselage was covered with flush-riveted duralumin, while the wing had a stressed plywood skin. 


The F.5 (standing for Fabrizi 5) had a two-row 14-cylinder Fiat A.74 R.C. 38 radial engine, unlike its cousin the F.4, which Fabrizi and his design team intended to be powered by a water-cooled engine. The F.4 project was not pursued immediately because the Italian Air Ministry held its proposed engine in disfavor, but development of the F.5 continued.

The F.5 prototype first flew on 19 February 1939. The aircraft displayed very high maneuverability during official testing, prompting an order for both a second prototype and 12 preproduction models. The last of the preproduction aircraft was selected for use as a prototype in a renewed F.4 program, but the rest of the F.5 order was delivered to the Regia Aeronautica (Italian Royal Air Force).


No F.5 production models were built as Caproni decided to produce the more developed Caproni Vizzola F.6M fighter instead.

The Regia Aeronautica assigned the 11 preproduction F.5 fighters to the 300° Squadriglia, 51° Stormo for operational use. By 1942, they were serving as night fighters in the 167° Gruppo.
                
The F.5 was offered to foreign customers. It has been said that the Aeroplani Caproni subsidiary in Peru acquired the license rights for local manufacture, but no F.5s were ever built in Peru.
General characteristics
Length: 7.90 m 
Wingspan: 11.3 m 
Height: 3 m 
Wing area: 17.6 m2 
Empty weight: 1,850 kg 
Gross weight: 2,238 kg 
Powerplant: 1 × Fiat A.74 R.C.38 14-cyl. air-cooled radial piston engine, 649 kW (870 hp) at take-off
Maximum speed: 510 km/h 
Range: 770 km at 455 km/h 
Service ceiling: 9,500 m 
Time to altitude: 6,500m  in 6min 30s

Guns: 2 × 12.7 mm (0.5 in) forward-firing Breda-SAFAT machine guns

lauantai 12. toukokuuta 2018

Aeronautica Umbra Trojani - AUT.18

The AUT.18 was a prototype fighter aircraft developed in Italy by Aeronautica Umbra shortly before the outbreak of World War II. It was designed in 1934 by Ing Felice Trojani, who at that time was collaborating with Umberto Nobile on the Arctic flights of the airships Norge and Italia. The aircraft's designation came from initials of the manufacturer, the surname of the designer, and the aircraft's wing area (18 m²), the sole prototype receiving the serial no. M.M.363.
               Aut18-i.jpg
Born from the same Regia Aeronautica requirement that spawned the Caproni-Vizzola F.5, FIAT G.50, Macchi C.200, Meridionali Ro 51 and Reggiane Re 2000 fighters, the A.U.T.18 flew for the first time on 22 April 1939, powered by a 1,044 hp (778.51 kW) Fiat A.80 R.C.41 radial engine. The fighter had an all-metal stressed-skin structure, covered in duralumin, featuring an inwardly-retracting undercarriage and retractable tail-wheel and was armed with two 12.7 mm Breda-SAFAT machine-guns mounted in the wings just outboard of the undercarriage.

Flight trials proved disappointing and lagged behind the other fighters in Progetto R - the modernisation (riammodernamento) of the Regia Aeronautica. With no production orders forthcoming, despite the prototype being returned to the Umbra factory at Foligno for modifications on 20 February 1940 and a second flight test series from 5 November 1940, no improvement was demonstrated over fighters already in production so the A.U.T.18 was abandoned.

After delivery to the Regia Aeronautica on 5 November 1940 the fate of the prototype is not known, possibly being transferred to Germany for evaluation, it was also rumoured to have been captured by British forces, but it is more likely that it was destroyed in a raid after its transfer to Orvieto.
                  Kuvahaun tulos haulle Aeronautica Umbra Trojani AUT.18

General characteristics
Crew: 1
Length: 8.56 m 
Wingspan: 11.5 m 
Height: 2.88 m 
Wing area: 18.70 m2 
Empty weight: 2,320 kg 
Gross weight: 2,975 kg 
Powerplant: 1 × Fiat A.80 R.C.41, 780 kW (1,044 hp)
Maximum speed: 480 km/h 
Range: 800 km 
Service ceiling: 10,000 m 
Armament: 2 x 12.7 mm Breda-SAFAT machine guns