ALLAH NAMES

Wednesday, March 16, 2011

Macchi C.200

C.200 Saetta
Preserved C.200 in the markings of 372° Sq. Regia Aeronautica
Role Fighter
Manufacturer Aeronautica Macchi
First flight 24 December 1937
Introduced 1939
Retired 1947
Primary user Regia Aeronautica
Number built 1,153
The Macchi C.200 Saetta (also variously identified as the MC.200) (Italian: Thunderbolt) was a World War II fighter aircraft built by Aeronautica Macchi in Italy, and used in various forms throughout the Regia Aeronautica (Italian Air Force). The MC.200 had excellent manoeuvrability and general flying characteristics left little to be desired.[1] Stability in a high-speed dive was exceptional,[2] but it was underpowered and underarmed for a modern fighter.[3]
From the time Italy entered war on 10 June 1940, until her surrender on 8 September 1943, the Macchi C. 200 flew more operational sorties than any Italian aircraft. The Saetta ranged over Greece, North Africa, Yugoslavia, across the Mediterranean and Russia (where it obtained an excellent kill to loss ratio of 88 to 15).[4][5] Its very strong all-metal construction and air-cooled engine made the aircraft ideal for ground attack and several units flew it as a fighter-bomber. Over 1,000 were built by the time the war ended.[6]

Contents

  • 1 Design and development
  • 2 Production
  • 3 Operational history
    • 3.1 Yugoslavia
    • 3.2 North Africa
    • 3.3 Eastern Front
    • 3.4 After the armistice
  • 4 Variants
  • 5 Operators
  • 6 Specifications (Macchi C.200 early series)

Design and development

C.200 prototype
Following the end of Italy's campaigns in East Africa, a program was started to completely re-equip the Regia Aeronautica with a new interceptor aircraft of modern design. The 10 February 1936 specifications [7] called for an aircraft powered by a single radial engine, with a top speed of 500 km/h, climb rate at 6,000 meters of 5 minutes, with a flight endurance of two hours, and armed with a single (later increased to two) 12.7 mm (0.5 in) machine gun.[8]
Macchi's lead designer was Mario Castoldi, the creator of several racing aircraft which competed for the Schneider Trophy, including the M.39, which won the competition in 1926. He also designed the M.C. 72. In designing a modern fighter, Castoldi proposed a modern all-metal cantilever low-wing monoplane, with retractable landing gear, and an enclosed cockpit. The fuselage was of semi-monocoque construction, with self-sealing fuel tanks under the pilot's seat, and in the centre section of the wing. The distinctive "hump" elevated the cockpit to provide the pilot with an unobstructed view over the engine. The wing had an advanced system whereby the hydraulically-actuated flaps were interconnected with the ailerons, so that when the flaps were lowered the ailerons drooped as well.
Power was provided by the 650 kW (870 hp) Fiat A.74 radial engine, although Castoldi preferred inline engines, and had used them in all of his previous designs. With "direttiva" (Air Ministry Specific) of 1932, Italian industrial leaders had been instructed to concentrate solely on radial engines for fighters, due to their better reliability.[9] The A.74 was a re-design of the American Pratt & Whitney R-1830 SC-4 Twin Wasp made by engineers Tranquillo Zerbi and Antonio Fessia and was the only Italian engine that could provide a reliability similar to Allied products.[10]
The licence-built A.74 engine could be problematic. In late spring 1941, 4° Stormo's Macchi C.200s then based in Sicily, had all the A.74s produced by the Reggiane factory replaced because they were defective units. The elite unit had to abort many missions against Malta due to engine problems.[11] Although the Macchi C.200 was considered underpowered, the air-cooled radial engine made it suitable for ground attack. Consequently, the C.200 was often used as a cacciabombardiere (fighter-bomber).[12] Moreover, it was maneuverable and had a sturdy all-metal construction. Its armament of two 12.7 mm (.5 in) machine guns was not sufficient, but the Saetta could compete with contemporary Allied fighters.
The first prototype (MM.336) C.200 flew on 24 December 1937, in Lonate Pozzolo, Varese, with Macchi Chief Test Pilot Giuseppe Burei at the controls. It was followed by the second prototype early the next year. During testing, the aircraft attained 805 km/h (500 mph) in a dive, although it could muster only 500 km/h (310 mph) in level flight due to a lack of engine power. Nevertheless, this was better than the performance of the competing Fiat G.50, Reggiane Re.2000, A.U.T. 18, IMAM Ro.51, and Caproni-Vizzola F.5. In 1938 the C.200 won the tender "Caccia I" (fighter 1st) of the Regia Aeronautica, even if after tests at Guidonia airport, on 11 June 1938, Maggiore Ugo Borgogno had warned that when turning at 90° and the pilot tried to make a tighter turn, the aircraft became extremely difficult to control, tending to turn upside down, mostly to the right and entering into a violent flat spin.[4] Nevertheless, an initial order for 99 was placed to Macchi factory. The G.50 (which in same flight tests at Guidonia airport out-turned the Macchi [4]) was also placed in limited production, because it could be brought into service earlier. Production started in June 1939.
Like other of the early Italian monoplanes, the C.200 suffered from a dangerous tendency to go in a spin.[13] Early production C.200 aircraft showed autorotation problems similar to the ones of the Fiat G.50, IMAM Ro.51, and the AUT 18. At the beginning of 1940 two deadly accidents occurred due to autorotation. Deliveries and production stopped, and the Regia Aeronautica thought of abandoning use of the type, as the skill involved in flying it was beyond that of the average pilot.[14] The problem was the new profile of the wing. Castoldi soon tested a new profile, but a solution to the autorotation problem was found by Sergio Stefanutti, chief designer of SAI Ambrosini in Passignano sul Trasimeno, based on studies by Willy Messerschmitt and the NACA. He redesigned the wing section according to variable (instead of constant) profile[15] by just covering parts of the wings with plywood.[4]
The new wing entered production in 1939/1940 at SAI Ambrosini and became a standard on the aircraft manufactured by Aermacchi and Breda, a licenced manufacturer.[16] After the modified wings of the Saetta were introduced, the C.200 proved to be, for a time, the best Italian fighter. To save weight, the first production C.200 series did not have armour fitted to protect the pilots. Armour plating was incorporated when the units were going to replace the Saettas with the new Macchi C.202 Folgore and often in only a limited number of aircraft. After the armour was fitted, the aircraft could become difficult to balance, and during aerobatic manoeuvres could enter an extremely difficult to control flat spin, forcing the pilot to bail out. On 22 July 1941, Leonardo Ferrulli, one of the top-scoring Regia Aeronautica pilots, encountered the problem and was forced to bale out over Sicily.[17] At the beginning of 1940, Denmark was set to place an order for 12 C.200s, a deal that fell through when Germany invaded Denmark.

Production

The most serious handicap was the low production rate of the type at over 22,000 hours in production time due to antiquated construction technology.[18] A total of 1,153 Saettas were eventually produced, but almost all were gone by the time of the armistice between Italy and Allied armed forces in September 1943.
In an attempt to improve performance, a C.201 prototype was created with a 750 kW (1,000 hp) Fiat A.76 engine, but this was abandoned in favour of the Daimler-Benz DB 601-powered C.202. The Saetta was to have been replaced outright by the C.202 after only one year in production, but the C.200's service life was extended because Alfa Romeo could not produce enough of the RA.1000 (license-built DB 601) engines, and more C.200s were built using C.202 parts while waiting for production to increase.

Operational history

A Macchi C.200 on the ground
In August 1939 about 30 C.200s, by then nicknamed Saetta ("Arrow"), were delivered to 10° Gruppo of 4° Stormo, stationed in North Africa. Pilots of this "'elite" unit of the Regia Aeronautica opposed the adoption of the C.200, preferring the more manouvrable Fiat CR.42. These Saettas were then transferred to 6° Gruppo of 1° Stormo in Sicily (enthusiastic supporters of the new fighter) and Gruppo 152° of 54° Stormo in Vergiate. When Italy entered the war on 10 June 1940, 144 Macchis were operational, half of which serviceable.[4] Although the first 240 aircraft had fully-enclosed cockpits, the subsequent variants were given open cockpits at the request of the Italian pilots.[19]
The first Macchi C.200s to make their combat debut were those of the 6° Gruppo Autonomo C.T. led by Tenente Colonnello (Wing Commander) Armando Francois. This Squadron was based at the Sicilian airport of Catania Fontanarossa. A Saetta from this unit was the first C.200 to be lost in combat when on 23 June 1940 14 Macchis (eight from 88a Squadriglia, five from 79a Squadriglia and one from 81a Squadriglia) that were escorting 10 SM.79s from 11° Stormo were intercepted by two Gloster Gladiators. Gladiator N5519, piloted by Flt Lt George Burges, attacked the bombers but was in turn attacked by a C.200 flown by Sergente Maggiore Lamberto Molinelli of 71a Squadriglia over the sea off Sliema. The Macchi overshot four or five times the more agile Gladiator which eventually shot down the Saetta.[20]
C.200 in flight
Only on 1 November were the C.200s credited with their first kill. A Sunderland on a reconnaissance mission was sighted and attacked just outside Augusta by a flight of Saettas on patrol. [21] With the arrival towards the end of December 1940 of X Fliegerkorps in Sicily, the C.200s were assigned escort duty for I/StG.1 and II/StG.2 Ju 87 bombers attacking Malta, as the Stukas did not have adequate fighter cover until the arrival of 7./JG26's Bf 109s.[22]
On 6 February 1941, the elite unit 4° Stormo received C.200s from 54° Stormo. With the autorotation problems solved, the Macchis were regarded as "very good machines, fast, manoeuvrable and strong" by Italian pilots.[23] After intense training, on 1 April 1941, the 10° Gruppo (4° Stormo) moved to the Ronchi dei Legionari airport and started active service.[24] In combat with the less manoueverable Hurricane, it proved effective, with outstanding dogfight performance and no vices.[25] When it entered service, the Supermarine Spitfire was the only Allied fighter that it faced, which could outclimb the Saetta.[6]

Yugoslavia

C.200s from 4° Stormo took part in operations against Yugoslavia right from the start of hostilities. On the dawn of 6 April 1941, four C.200s from 73a Squadriglia flew over Pola fortress and attacked an oil tanker ship, setting it on fire. The 4° Stormo flew its last mission against Yugoslavia on 14 April: on that day, 20 C.200s from 10° Gruppo flew up to 100 km south of Karlovac without meeting any enemy aircraft. Operations ended on 17 April. During those 11 days, the 4° Stormo had not lost a single C.200. Its pilots destroyed 20 seaplanes and flying boats, damaging 10 more. In total, they had set on fire an oil tanker, a fuel truck, several other vehicles and destroyed port installations.[26]

North Africa

Fitted with dust filters and designated C.200AS, Saettas saw extensive use in North Africa. The Macchi's introduction was not well received by pilots when in 1940, the first C.200 unit, 4° Stormo replaced the type with the C.R.42. The first combat missions were flown as escorts for Savoia-Marchetti SM.79 bombers attacking Malta in June 1940, where one C.200 was claimed by a Gladiator. On 11 June 1940, second day of war for Italy, the C.200s of 79a Squadriglia encountered one of the Sea Gladiators which had been scrambled from Hal Far, Malta. Officer W.J. Wood claimed Tenente Giuseppe Pesola had been shot down, but the Italian pilot came back unscathed to his base.[27]
The Saetta with its sturdy construction, and its agility permitted skilled pilots to effectively fight against more modern designs like the British Hawker Hurricane and the American Curtiss P-40. Its greatest weakness was the light armament of two 12.7 mm (.5 in) Breda-SAFAT machine guns.[19]
While the Hurricane was faster at sea level (450 km/h/280 mph vs the C.200's 430 km/h/270 mph), the Saetta could reach more than 500 km/h (310 mph) at 4,500 m (14,800 ft), although speed dropped off at altitude: 490 km/h (300 mph) at 6,000 m (19,700 ft) and 350 km/h (220 mph) at 7,000 m (23,000 ft) with a maximum ceiling of 8,800 m (29,000 ft). Comparative speeds of the Hurricane Mk I was 505 km/h (314 mph) at 5,000 m (16,400 ft) and 528 km/h (328 mph) at 6,000 m (19,700 ft).[28] Over 5,000 m (16,400 ft) and at very low levels, only the huge Vokes (anti-sand) air filter fitted to the "tropical" variants slowed the Hurricane Mk II to Macchi levels. Although the Macchi C.200 was more agile than the Hurricane, it was lightly armed, its windshield and pilot's seat were not normally armoured nor was a radio fitted as standard, while its flight characteristics, even if better than the G.50, were not easily mastered by the average Italian pilot.
On 8 December 1941, Macchi MC.200s of the 153° Gruppo engaged Hurricanes from 94 Squadron. A violent dogfight developed with the commanding officer, Squadron Leader Linnard attempting to intercept a Macchi attacking a Hurricane. Both aircraft were making steep turns and losing height, but Linnard was too late and the Macchi, turning inside the Hurricane, had already hit the cockpit area. The stricken aircraft turned over at low level and dived into the ground, bursting into flames. Its pilot, the New Zealand born RAF "ace" (six enemy aircraft destroyed and many more probably destroyed) Flight Lieutenant Owen Vincent Tracey was killed.[4][29]
In same areas, C.200s operated as fighter-bombers against land and naval objectives, and sank the British destroyers HMS Zulu,and HMS Sikh near Tobruk, September 1942.
The C.200 subsequently saw action over Greece, Yugoslavia and the Balkans, frequently engaged in dogfights with British Hurricanes and Gladiators on the Balkans.[4]

Eastern Front

In August 1941, the Italian air force command sent one air corps, formed of 22º Gruppo Autonomo Caccia Terrestre with four squadrons and 51 C.200s to the Eastern Front with the Italian Air Force Expeditionary Corps in Russia (Corpo Italiano di Spedizione in Russia).[30] Together with C.202s, they claimed 88 to 15 victory/loss ratio.[19] The first Macchis arrived in Tudora, near Odessa, on 13 August 1941, commanded by Major (Maggiore) Giovanni Borzoni and deployed in 359a, 362a, 369a and 371a Flights (Squadriglias). Macchi pilots carried out their first operations from Krivoi Rog, on 27 August 1941, achieving eight aerial victories over Soviet bombers and fighters.[31] For a short time the 22° Gruppo was subordinated to Luftwaffe V.Fliegerkorps.[32] Subsequently, they took part in the September offensive on Dnjepr River, as the offensive went on, they operated sporadically from airstrips in Zaporozhye, Stalino, Borvenkovo, Voroshilovgrad, Makiivka, Oblivskaja, Millerovo and the most eastern location, Kantemirovka. The Italians moved to Zaporozhye late in October 1941. In December 371a Squadriglia was transferred to Stalino but replaced two days later by 359a with 11 Macchis. On 25 December, the C.200s flew low-level attacks against Soviet troops that had beleguered the Black Shirt (Camicie Nere)Legion Tagliamento, at Novo Orlowka. And on 28 December, pilots of 359a claimed nive Soviet aircraft, including six I-16 fighters, in the Timofeyevka and Polskaya area, without loss.[32]
During February 1942, the C.200 was employed in attacking Russian airfields at Kranyi Liman, Luskotova and Leninski Bomdardir. On 4 May 1942, the 22º Gruppo Autonomo Caccia Terrestre, that had reached its operational limit, was replaced by the newly formed 21º Gruppo Autonomo Caccia Terrestre, composed of 356ma, 382ma, 361ma and 386ma Squadriglia. This unit, commanded by Maggiore (Major) Ettore Foschini, brought new C.202s and 18 new Macchi C.200 fighters. During the second Battle for Kharkov (12–30 May), the Italians flew escort for the German bombers and reconnaissance aircraft.[33] In May, the Macchi's pilots received praise from the commander of the German 17th Army, mostly for their daring and effective attacks in the Slavyansk area.[34] During the German advance, in summer 1942, 21° Gruppo Autonomo C.T. transferred to Makeyevka airfield, and then to Voroshilovgrad and Oblivskaya. Increasingly, the Macchis were tasked to escort German aircraft and on 25 and 26 July 1942, five C.200s were lost in aerial combat.[35]
The following winter, the Soviet counter-offensive resulted in a retreat of the Axis forces. By early-December, only 32 Saettas were still operating, along with 11 Macchi C.202s. The losses grew in the face of a more aggressive enemy flying newer aircraft. The last major action was on 17 January 1943: 25 Macchis strafed enemy troops in the Millerovo area. The aviation of the ARMIR was withdrawn on 18 January, bringing 30 Macchi C.200 and nine C.202 fighters back to Italy and leaving 15 unserviceable aircraft behind. A total of 66 Italian aircraft had been lost on Eastern Front - against, according to official figures, 88 victories claimed during 17 months of action in that theater.[36]
The summary of Corpo Italiano di Spedizione in Russia operations included: 2,557 offensive flights (of which 511 with bombs dropping), 1.310 strafing attacks, 1.938 escort missions, 15 Saettas lost in combat. The top scoring unit was 362a Squadriglia commanded by Captain (Capitano) Germano La Ferla, that claimed 30 Soviet aircraft shot down and 13 destroyed on the ground.[37]

After the armistice

Twenty-three Saettas were transferred to Allied airfields in southern Italy, and flown for a short time by pilots of the Italian Co-Belligerent Air Force (Aviazione Cobelligerante Italiana, or ACI). A small number also flew for the pro-German National Republican Air Force (Aeronautica Nazionale Repubblicana, or ANR) based in northern Italy.

Variants

The Saetta underwent very few modifications during its service life. Aside from the switch to an open canopy, later aircraft were fitted with an upgraded radio and an armoured seat. Some late-production Saettas were built with the MC.202 Serie VII wing, thus adding two 7.7 mm (.303 in) Breda-SAFAT machine guns to the armament. The four (including two proposed) C.200 derivatives were:
M.C. 200 (prototypes)
Two prototypes fitted with the 623 kW (840 hp) Fiat a.74 RC 38 radial piston engine.
M.C. 200
Single-seat interceptor fighter, fighter-bomber aircraft. Production version.
M.C.200bis
Breda-proposed modification with a Piaggio P.XIX R.C.45 engine producing 880 kW (1,180 hp) at 4,500 m (14,800 ft). Converted from an early production C.200: first flight 11 April 1942 from Milano-Bresso flown by Luigi Acerbi. The aircraft was then fitted with a larger propeller and a revised engine cowling. Top speed in trials was 535 km/h (332 mph). It did not enter production as the C.200 had been replaced by more advanced designs.
M.C.200AS
Adapted version to North African Campaign.
M.C.200CB
Fighter-bomber version with 320 kg (710 lb) of bombs or two external fuel tanks (fighter escort).
M.C.201
As an answer to a 5 January 1938 request by the Regia Aeronautica for a C.200 replacement, Aermacchi proposed the C.201, with a revised fuselage, an engine Isotta-Fraschini Astro A.140RC.40 (license variant of the French Gnome-et-Rhone GR.14Krs Mistral Masjor) with 870CV. But later the choice was for the Fiat A.76 R.C.40 engine with 750 kW (1,000 hp). Two prototypes were ordered. The first flew on the 10 August 1940, still with the less powerful engine A.74.[38] Although Macchi estimated a top speed of 550 km/h (340 mph), the prototype was cancelled after Fiat abandoned the troublesome A.76 engine.

Operators

 Germany
 Italy

Specifications (Macchi C.200 early series)

Data from [19] and[39]
General characteristics
  • Crew: 1
  • Length: 8.25 m (27 ft 1 in)
  • Wingspan: 10.58 m (34 ft 8 in)
  • Height: 3.05 m (10 ft 0 in)
  • Wing area: 16.82 m² (181.00 ft²)
  • Empty weight: 1,964 kg (4,330 lb)
  • Loaded weight: 2,200 kg (4,840 lb)
  • Max takeoff weight: 2,395 kg (5,280 lb)
  • Powerplant:Fiat A.74 R.C.38 14-cylinder air-cooled radial engine, 650 kW (870 hp) at 2,520 rpm for takeoff
Performance
Armament
  • 2× 12.7 mm (.5 in) Breda-SAFAT machine guns, 370 rpg
  • Some aircraft were field-modified to carry up to 8× 15 kg (33 lb) or 2× 50, 100, or 150 kg (110, 220, or 330 lb) bombs under the wings

Lockheed YF-22

YF-22 "Lightning II"
Role Prototype fighter
National origin United States
Manufacturer Lockheed Corporation / Boeing / General Dynamics
First flight 29 September 1990
Primary user United States Air Force
Developed into Lockheed Martin F-22 Raptor
The Lockheed/Boeing/General Dynamics YF-22 was a prototype fighter aircraft designed for the United States Air Force. The YF-22 was a finalist in the United States Air Force's Advanced Tactical Fighter competition, and examples were built. The YF-22 won the contest against the Northrop YF-23, and entered production as the Lockheed Martin F-22 Raptor. The YF-22 is similar to the F-22, but with differences in the cockpit, tail fins and wings.




Contents

  • 1 Design and development
  • 2 Specifications (YF-22)

Design and development

The USAF's Advanced Tactical Fighter (ATF) program was conceived in the early 1980s, to provide a replacement for the F-15 Eagle.[1] The Air Force issued a request for proposals (RFP) for the fighter in September 1985, then modified the RFP to include flying prototypes in the final selection.[2] Proposals were submitted by Boeing, General Dynamics, Lockheed, Northrop, and McDonnell Douglas in July 1986.[3] Lockheed and Northrop were selected in October 1986 for the demonstration phase, ending in a flyoff of prototypes. The companies had previously agreed to form the Lockheed/ General Dynamics/Boeing team and Northrop/McDonnell Douglas team.[4]
The Lockheed team designed the YF-22 and the Northrop team designed the YF-23. Two examples of each prototype were built for the Demonstration-Validation phase: one with General Electric YF120 engines, the other with Pratt & Whitney YF119 engines.[5][6]
The YF-22 was given the unofficial name "Lightning II", after the World War II fighter P-38, by Lockheed, which persisted until the mid-1990s when the USAF officially named the aircraft "Raptor".[7] The F-35 later received the Lightning II name in 2006.[8]
The YF-22 first flew on 29 September 1990.[9] Flight testing began afterwards and added the second aircraft for each competitor in late October 1990.[10] The YF-22 with GE engines achieved Mach 1.58 in supercruise.[11] Flight testing continued until December 1990. Following flight testing, the contractor teams submitted proposals for ATF production.[10]

Specifications (YF-22)

Note some specifications are estimated.




Lockheed YF-22 3-view diagram

Saturday, March 12, 2011

Lockheed YF-12

YF-12
YF-12A undergoing flight testing.
Role Interceptor
Manufacturer Lockheed Corporation
Designed by Clarence "Kelly" Johnson
First flight 7 August 1963
Status Cancelled
Primary user United States Air Force
Number built 3
Unit cost US$15-18 million (projected)[1]
Developed from Lockheed A-12
The Lockheed YF-12 was an American prototype interceptor aircraft, which the United States Air Force evaluated as a development of the highly-secret Lockheed A-12 that also spawned the now well known SR-71 Blackbird.



Contents

  • 1 Design and development
  • 2 Operational history
    • 2.1 USAF testing
    • 2.2 NASA testing
  • 3 Variants
  • 4 Operators
  • 5 Specifications (YF-12A)
  • 6 Aircraft disposition

Design and development

In the late 1950s the United States Air Force (USAF) sought a replacement for the F-106 Delta Dart. As part of the Long Range Interceptor Experimental (LRI,X) program, North American Aviation's F-108 proposal, a Mach 3-capable interceptor was selected. However, the F-108 was canceled in September 1959.[2] During this time Lockheed's Skunk Works was developing the A-12 spy plane for the Central Intelligence Agency (CIA) under the Oxcart program. Skunk Works' Kelly Johnson proposed a version of the A-12 called AF-12 by the company and the USAF ordered three AF-12s in mid-1960.[3]
The AF-12s would take the seventh through ninth slots on the A-12 production line and have them completed in the YF-12A interceptor configuration.[4] The main changes involved modifying the aircraft's nose to accommodate the Hughes AN/ASG-18 fire-control radar originally developed for the XF-108, and the addition of a second cockpit for a crew member to operate the fire control radar. The nose modifications changed the aircraft's aerodynamics enough to require ventral fins to be mounted under the fuselage and engine nacelles to maintain stability. Finally, four bays previously used to house the A-12's reconnaissance equipment were converted to carry Hughes AIM-47 Falcon (GAR-9) missiles.[5] One bay was used for fire control equipment.[6]
The first YF-12A flew on 7 August 1963.[5] President Lyndon B. Johnson announced the existence of the plane[7][8] on 24 February 1964.[9][10] The YF-12A was announced in part to continue hiding the A-12, its still-secret ancestor; any sightings of CIA/Air Force A-12s based at Area 51 in Nevada could be attributed to the well-publicized Air Force YF-12As based at Edwards Air Force Base in California.[8]
On 14 May 1965 the Air Force placed a production order for 93 F-12Bs for its Aerospace Defense Command (ADC).[11] However, Secretary of Defense Robert McNamara would not release the funding for three consecutive years due to Vietnam War costs.[11] Updated intelligence placed a lower priority on defense of the continental US, so the F-12B was deemed as being no longer needed. Then in January 1968, the F-12B program was officially ended.[12]

Operational history

USAF testing

YF-12A
During flight tests the YF-12As set a speed record of 2,070.101 mph (3,331.505 km/h) and altitude record of 80,257.86 ft (24,462.6 m), both on 1 May 1965,[9] and demonstrated promising results with their unique weapon system. Six successful firings of the AIM-47 missiles were completed. The last one launched from the YF-12 at Mach 3.2 at an altitude of 74,000 ft (22,677 m) to a JQB-47E target drone 500 ft (152 m) off the ground.[13]
The program was abandoned following the cancellation of the production F-12B, but the YF-12s continued flying for many years with the USAF and with NASA as research aircraft.

NASA testing

YF-12A #60-06935 in the National Museum of the USAF
The initial phase of this program included test objectives aimed at answering some questions about implementation of the B-1. Air Force objectives included exploration of its use in a tactical environment, and how AWACS would control supersonic aircraft. The Air Force portion was budgeted at US$4 million. The NASA tests would answer questions such as how engine inlet performance affected airframe and propulsion interaction, boundary layer noise, heat transfer under high Mach conditions, and altitude hold at supersonic speeds. The NASA budget for the 2.5-year program was US$14 million.[14]
Of the three YF-12As, #60-6934 was damaged beyond repair by fire at Edwards during a landing mishap on 14 August 1966; its rear half was salvaged and combined with the front half of a Lockheed static test airframe to create the one and only SR-71C. That aircraft was nicknamed "The Bastard" by its pilots, as it did not fly quite straight. It is unique among SR-71s as it retained the ventral fins under its nacelles from its YF-12 lineage.
YF-12A #60-6936 was lost on 24 June 1971 due to an inflight fire caused by a failed fuel line; both pilots ejected safely just north of Edwards AFB. YF-12A #60-06935 is the only surviving YF-12A; it was recalled from storage in 1969 for a joint USAF/NASA investigation of supersonic cruise technology, and then flown to the National Museum of the United States Air Force at Wright-Patterson Air Force Base near Dayton, Ohio on 17 November 1979.[9]
A fourth YF-12 aircraft, the "YF-12C", was actually the second SR-71A (61-7951). This SR-71A was re-designated as a YF-12C and given a fictitious serial number 60-6937 from an A-12 to maintain SR-71 secrecy. The YF-12C was loaned to NASA for propulsion testing after the loss of YF-12A (60-6936) in 1971. The YF-12C was operated by NASA until September 1978, when it was returned to the Air Force.[15]

Variants

YF-12A 
Pre-production version. Three were built.[16]
F-12B 
Production version of the YF-12A; canceled before production could begin.[17]
YF-12C 
Fictitious designation for a SR-71 provided to NASA for flight testing. The YF-12 designation to keep SR-71 information out of the public domain.[18]

Operators

 United States

Specifications (YF-12A)

Orthographically projected diagram of the Lockheed YF-12.
Data from Lockheed's SR-71 'Blackbird' Family[19]
General characteristics
Performance
Armament
Avionics
  • Hughes AN/ASG-18 look-down/shoot-down fire control radar

Aircraft disposition

List of YF-12s
Serial number Model Location or fate
60-6934 YF-12A Transformed into SR-71C 61-7981 after fire damage in 1966,
on display at Hill Aerospace Museum, Hill AFB, UT
60-6935 YF-12A National Museum of the U.S. Air Force, Wright-Patterson AFB, OH
60-6936 YF-12A Lost, 24 June 1971
The sole remaining YF-12A is located at the National Museum of the United States Air Force, at Wright-Patterson Air Force Base, near Dayton, Ohio.[9] This aircraft has small patches in its skin, on the starboard side below the cockpit. The patches cover holes caused by the "spurs" of a crewman who had to evacuate the plane after an emergency landing. The "YF-12C" (actually SR-71A, serial 61-7951) is on display at the Pima Air Museum in Tucson, AZ as of 2005.[15]

Lockheed XF-90

XF-90
XF-90 in flight
Role Fighter
Manufacturer Lockheed
Designed by Willis Hawkins
Clarence L. "Kelly" Johnson
First flight 3 June 1949
Status Cancelled
Number built 2
Unit cost US$5.1 million for the program[1]
The Lockheed XF-90 was built in response to a United States Air Force requirement for a long-range penetration fighter and bomber escort. The same requirement produced the McDonnell XF-88 Voodoo. Lockheed received a contract for two prototype XP-90s ( redesignated XF-90 in 1948). The design was developed by Willis Hawkins and the Skunk Works team under Kelly Johnson. Two prototypes were built (s/n 46-687 and -688). Developmental and political difficulties delayed the first flight until 3 June 1949, with Chief Test Pilot Tony LeVier at the controls. Performance of the design was considered inadequate due to being underpowered, and the XF-90 never entered production.

Contents

  • 1 Design and development
  • 2 Testing and evaluation
  • 3 Specifications (XF-90A)

Design and development

After a redesign from its original delta planform, the Lockheed Model 90 was built as a mock-up in 1947.[2]The final design featured 35° sweptback wings, a sharply-pointed nose and two Westinghouse J34-WE-11 axial-flow turbojet engines, providing a total thrust of 6,200 lbf (27.6 kN),mounted side-by-side in the rear fuselage and fed by side-mounted air intakes. [3]The wings had leading-edge slats, Fowler flaps and ailerons on the trailing edge. The pressurized cockpit was fitted with an ejector seat and a bubble canopy. Proposed armament was six 20  mm (.79 in) cannons. The internal fuel was supplemented by wingtip-mounted tanks, bringing total fuel capacity to 1,665 gal (6,308 l). The use of 75ST aluminum rather than the then-standard 24ST aluminum alloy, along with heavy forgings and machined parts, resulted in an extremely well-constructed and sturdy airframe. However, these innovations also resulted in an aircraft which had an empty weight more than 50 percent heavier than its competitors.[3]
The first XF-90 used J34s without afterburning, while the second (XF-90A) had afterburners installed; these were tested on an F-80 testbed, yet the aircraft remained underpowered. [3]

Testing and evaluation

The first XF-90 prototype.
The XF-90 was the first USAF jet with an afterburner and the first Lockheed jet to fly supersonic, albeit in a dive. It also incorporated an unusual vertical stabilizer that could be moved forward and backward for horizontal stabilizer adjustment. Because Lockheed's design proved underpowered, McDonnell's XF-88 won the production contract in September 1950.
Upon Lockheed losing the production contract, the two prototypes were retired to other testing roles. The first aircraft (46-687) was shipped to the NACA Laboratory in Cleveland, Ohio in 1953 for structural tests. It was no longer flyable, and its extremely strong airframe was tested to destruction. The other (46-688) survived three atomic blasts at Frenchman Flat within the Nevada Test Site in 1952. The XF-90 lived on in popular culture as the aircraft of the "Blackhawks" comic book.
In 2003, the heavily damaged hulk of the second XF-90A (46-688) was recovered from the Nevada test site and moved to the National Museum of the United States Air Force in Dayton, Ohio. It is currently undergoing minor restoration in one of the Museum's restoration facility hangars. Its wings have been removed, and its nose is mangled from the nuclear blasts. During the decontamination process, all the rivets had to be removed to remove radioactive sand. At present, the museum plans to display the XF-90 in its damaged, mostly unrestored condition, to demonstrate the effects of nuclear weaponry.

Specifications (XF-90A)

General characteristics
  • Crew: One
  • Length: 56 ft 2 in (17.12 m)
  • Wingspan: 40 ft 0 in (12.20 m)
  • Height: 15 ft 9 in (4.80 m)
  • Wing area: 345 ft² (32 m²)
  • Empty weight: 18,050 lb (8,204 kg)
  • Loaded weight: 27,200 lb (12,363 kg)
  • Max takeoff weight: 31,060 lb (14,118 kg)
  • Powerplant:Westinghouse J34-WE-15 turbojets, 4,100 lbf (18.2 kN) each
Performance
Armament
  • 6 × 20 mm (.79 in) cannons
  • 8 × 5 in (127 mm) HVAR rockets
  • Up to 2,000 lb (907 kg) of bombs

Lockheed XF-104

XF-104
The first prototype Lockheed XF-104 53-7786
Role Interceptor prototype
Manufacturer Lockheed Aircraft Corporation
Designed by Clarence L "Kelly" Johnson
First flight 4 March 1954
Primary users Lockheed
United States Air Force
Number built Two
Variants F-104 Starfighter
Lockheed NF-104A
Canadair CF-104
Aeritalia F-104S
CL-1200 Lancer/X-27
The Lockheed XF-104 was a single-engine, high-performance, supersonic interceptor aircraft designed as the prototype for a United States Air Force series of lightweight and simple fighters. Only two aircraft were built, one aircraft was used primarily for aerodynamic research and the other served as an armament testbed.[1] Both prototypes were destroyed in accidents during testing. The XF-104 was the forerunner of over 2,500 F-104 Starfighters.

Contents

  • 1 Development
    • 1.1 Design approval and competition
  • 2 Design
    • 2.1 Wing
    • 2.2 Tail surfaces
    • 2.3 Fuselage
    • 2.4 Ejection seat
    • 2.5 Differences between XF-104 and F-104 Starfighter
  • 3 Testing and evaluation
    • 3.1 First XF-104-LO
    • 3.2 Second XF-104-LO
    • 3.3 Testing conclusions
  • 4 Variants
  • 5 Operators
  • 6 Specifications (XF-104)

Development

An original Johnson sketch
Clarence L "Kelly" Johnson, chief engineer at Lockheed's Skunk Works, visited Korea in December 1951 and talked to fighter pilots about what sort of aircraft they wanted. At the time USAF pilots were confronting the MiG-15 "Fagot" in their F-86 Sabres, and many of the pilots felt that the MiGs were superior to the larger and more complex American design. The pilots requested a small and simple aircraft with excellent performance.[2]
One pilot in particular, Colonel Gabby Gabreski was quoted as saying; "I'd rather sight with a piece of chewing gum stuck on the windscreen" and told Johnson that Radar "was a waste of time".[2]
On his return to the U.S., Johnson immediately started the design of just such an aircraft realising that an official requirement would soon be published. In March 1952 his team was assembled, and they sketched several different aircraft proposals, ranging from small designs at 8,000 lb (3.6 t), to fairly large ones at 50,000 lb (23 t). The L-246 as the design became known remained essentially identical to the "Model L-083 Starfighter" as eventually delivered.[3]

Design approval and competition

The design was presented to the Air Force in November 1952, who were interested enough to create a new proposal, inviting several companies to participate. Three additional designs were received: the Republic AP-55, an improved version of its prototype XF-91 Thunderceptor; the North American NA-212, which would eventually evolve into the F-107; and the Northrop N-102 Fang, a new General Electric J79-powered design. Although all were interesting, Lockheed had an insurmountable lead and was granted a development contract in March 1953.[3]
Lockheed X-7
Test data from the earlier Lockheed X-7 unmanned ramjet/rocket program proved invaluable for aerodynamic research since the XF-104 would share the X-7's wing and tail planform and airfoil sections.[4][5] Experience gained from the Douglas X-3 Stiletto was also used in the design phase of the XF-104.[6] Over 400 surplus instrumented artillery rockets were launched to test various airfoils and tail designs; from which the camera film and telemetry were recovered by parachute.[7]
Wooden mock-up
Work progressed quickly, with a wooden mock-up ready for inspection at the end of April, and work started on two prototypes late in May. At the time, the J79 engine was not ready; so, both prototypes were designed to use the Wright J65 engine instead, a licensed built version of the Armstrong Siddeley Sapphire. Construction of the first prototype XF-104 (53-7786) began in summer 1953 at Lockheed's Burbank, California factory. This aircraft was powered by a non-afterburning Buick-built Wright J65-B-3 turbojet. The first prototype was completed by early 1954, and started flying in March. The total time from award of the contract to first flight was only one year, a very short time even then, and unheard of today, when ten to 15 years is more typical.[5]
Construction of the second prototype (53-7787) began in autumn 1953.

Design

Douglas X-3 Stiletto
In order to achieve the desired performance, Lockheed chose a minimalist approach: a design that would achieve high performance by wrapping the lightest, most aerodynamically efficient airframe possible around a single powerful engine. The emphasis was on minimizing drag and mass.[8]

Wing

The XF-104 had a radical wing design. Most jet fighters of the period (and to this day) used a swept-wing or delta-wing planform. This allowed a reasonable balance between aerodynamic performance, lift, and internal space for fuel and equipment. Lockheed's tests, however, determined that the most efficient shape for high-speed, supersonic flight was a very small, straight, mid-mounted, trapezoidal wing. The wing was extremely thin, with a thickness-to-chord ratio of only 3.36%. Its aspect ratio was 2.45. The leading edges of the wing were so thin (0.016 in/0.41 mm) and so sharp that they presented a hazard to ground crews, and protective guards had to be installed during ground operations. The thinness of the wings meant that fuel tanks and landing gear had to be contained in the fuselage. The hydraulic actuators driving the ailerons were only one inch (25 mm) thick to fit into the available space and were known as Piccolo actuators because of their resemblance to this musical instrument. The wings had electrically driven leading and trailing edge flaps to increase lift at low speed. The XF-104 did not feature the Boundary Layer Control System of the production aircraft.[9]

Tail surfaces

After extensive wind tunnel testing, the stabilator was mounted at the top of the fin for optimum stability and control about the pitch axis.[9] Because the vertical tail fin was only slightly shorter than the length of each wing and nearly as aerodynamically effective, it could act as a wing on rudder application (a phenomenon known as Dutch roll). To offset this effect, the wings were angled downward to give 10° anhedral. The rudder was manually operated and supplemented by a small yaw damper surface mounted at the bottom of the fin.[9]
First XF-104 (53-7786) on Rogers Dry Lake

Fuselage

The fuselage of the XF-104 had a high fineness ratio, i.e., tapering sharply towards the nose, and a small frontal area of 25 ft².[10] The fuselage was tightly packed, containing the cockpit, avionics, cannon, all internal fuel, landing gear, and engine.[8]
The air intakes, designed by Ben Rich, were of fixed geometry without inlet cones, since the J65-powered aircraft was incapable of Mach 2 performance. They were similar to those of the F-94 Starfire, being mounted slightly away from the fuselage, with an inner splitter plate for the boundary layer bleed air.
The combination of these features provided extremely low drag except at high angle of attack, at which point induced drag became very high.

Ejection seat

The XF-104 featured an unusual downward-ejecting Stanley B seat. It was feared that contemporary ejection seat designs would not have enough explosive power to clear the high "T" tail assembly. In the event of the seat not firing it was possible to manually release the lower fuselage hatch and then exit the aircraft via gravity. The F-104 series aircraft would later convert to upward-ejecting seats but the fuselage hatch was retained as a useful maintenance feature.[1][11]

Differences between XF-104 and F-104 Starfighter

Visible changes from the XF-104 to production versions of the Starfighter include a longer fuselage (to accommodate the J79 engine and extra internal fuel) and a forward-retracting nose landing gear (except two-seat versions) to increase clearance for the downward-ejecting seat. A ventral fin for increased stability was added during the YF-104A test programme. Inlet shock cones and a fuselage spine fairing between the canopy and fin that housed fuel piping were further added features.[3][12]

Testing and evaluation

Tony LeVier with an XF-104

First XF-104-LO

The first XF-104 (Lockheed 083-1001, USAF 53-7786) was taken by road to Edwards Air Force Base amidst high secrecy during the night of 24–25 February[3] where Lockheed test pilot Tony LeVier was to do the initial testing. On 28 February 1954, the XF-104 made a planned hop[13] of about five feet off the ground during a high-speed taxi, but its first official flight took place on 4 March 1954. During that flight, the landing gear would not retract, and LeVier landed after a low-speed flight of about 20 minutes. After adjustments, LeVier took off again but the landing gear still would not retract. The problem turned out to be low pressure in the hydraulic system. Bad weather kept the XF-104 on the ground until 26 March when further flights were carried out with the landing gear retracting normally.
Of the two aircraft, FG-786 was used primarily for aerodynamic testing and was the only XF-104 to be used for tip-tank carriage and jettison trials.
The yaw damper of the XF-104 was found to be ineffective and the rudder did not positively center, these problems were corrected by revising the rudder control system.[14]
The XF-104 was subsonic in level flight when powered by the non-afterburning J65, but Mach 1 could be easily exceeded during a slight descent. In July 1954, the J65-B-3 was replaced by the afterburning J65-W-7 turbojet. With this engine installed the performance of the XF-104 was greatly improved. Maximum level speed was Mach 1.49 at 41,000 ft (12,000 m), and an altitude of 55,000 ft (17,000 m) could be attained in a zoom climb, while Mach 1.6 could be attained in a dive. XF-104 number 1 achieved a top speed of Mach 1.79 at 60,000 feet (18,000 m) on 25 March 1955 with Lockheed test pilot J. Ray Goudey at the controls. This was the highest speed achieved by either of the XF-104 prototypes.[8] The first XF-104 was accepted by the USAF in November 1955.
XF-104 53-7786 was lost in a crash on 11 July 1957 when it developed an uncontrollable tail flutter while flying chase for F-104A flight tests. The entire tail group was ripped from the airframe, and Lockheed test pilot Bill Park was forced to eject. Vertical fin flutter was a known problem and the aircraft had been limited to speeds of no more than Mach 0.95 at the time of the accident. Tony LeVier had attempted to have the aircraft removed from flight status and placed in a museum, arguing that its performance was not suitable for chase duties.[15][16][17]

Second XF-104-LO

The second prototype (Lockheed 083-1002, USAF 53-7787), which was fitted with the afterburning J65 from the start, first flew on 5 October 1954. Since it was to be the armament test bed, it was fitted with the 20 mm (.79 in) M61 Vulcan cannon and was equipped with an AN/ASG-14T-1 fire control system.[12]
M61 Vulcan
Initial aerial firing tests with the Vulcan cannon were successful, but on 17 December, there was an explosion during a firing burst[15] and the J65 engine suffered severe compressor stalls. Test pilot Tony LeVier immediately shut down the engine and glided back to make a successful deadstick landing at Rogers Dry Lake. An investigation later showed that one of the 20 mm cannon rounds had exploded in the breech, blowing the bolt out the rear of the gun and through the structure into the forward fuselage fuel cell. Jet fuel had run into the gun bay, and leaked out of the compartment door seals and into the left engine air intake. The engine immediately flooded with fuel, causing the compressor stalls.
XF-104 53-7787 was lost on 14 April 1955 after accumulating over 1,000 flying hours[15][18] when test pilot Herman Salmon was forced to eject during gun firing trials at 50,000 ft (15,000 m). The gun malfunctioned during a test firing, and severe vibrations began to build up which knocked loose the ejection hatch below the cockpit. Cabin pressure was lost with Salmon's pressure suit inflating and covering his face so that he could not see. Recalling Tony LeVier's harrowing experience with the exploding cannon shell the previous December, Salmon believed that the same thing had happened to him and that he had no option but to eject. He later found out that he could have saved 53-7787 by simply bringing it down to a lower altitude and waiting for his pressure suit to deflate. With the loss of the armament testbed, Lockheed engineers were forced to find an alternative, and armament trials were continued on a modified Lockheed F-94C Starfire.[14] Consequently, no XF-104 prototype survives today.

Testing conclusions

XF-104 53-7786 with early models of the F-100, F-101 and F-102
Flight testing proved that performance estimates were accurate and that even when fitted with the low powered J65 engine, the XF-104 flew faster than the other Century Series fighters being developed at the time. The XF-104's ceiling at 60,000 ft (18,000 m) was 7,000 ft (2,100 m) higher than predicted, and it exceeded estimated speed and drag figures by two to three percent.[19] It was noted however that the low thrust of the J65 engine did not enable the full performance potential of the type to be realized..[15]
The unpowered rudder did not provide adequate directional control at high airspeeds (remedied by using hydraulic power on all subsequent versions of the F-104) and some concern was expressed over poor subsonic maneuverability at higher altitudes.[14]
Production aircraft would feature a redesigned fin structure using stainless steel spars to eliminate the flutter problem.[16] Since the internal fuel capacity was low limiting the useful range of the aircraft, extra capacity was provided on later versions by lengthening the forward fuselage.[15]
During a later interview Kelly Johnson was asked about his opinion on the aircraft, "Did it come up to my designs? In terms of performance, yes. In terms of engine, we went through a great many engine problems, not with the J65s but with the J79s."[20]
For his part in designing the F-104 airframe Johnson was jointly awarded the Collier Trophy in 1958, sharing the honor with General Electric (engine) and the U.S. Air Force (Flight Records).[21]

Variants

Official approval of the XF-104 design led to a contract for 17 YF-104A service test aircraft and a production run of over 2,500 aircraft built both in the United States and under license worldwide.[15]

Operators

 United States

Specifications (XF-104)

XF-104 3-view
Data from Bowman and Drendel.[1][22]
General characteristics
  • Crew: 1
  • Length: 49 ft 2 in (15 m)
  • Wingspan: 21 ft 11 in (6.69 m)
  • Height: 13 ft 6 in (4.1 m)
  • Wing area: 196 ft² (18.21 m²)
  • Airfoil: Bi-convex 3.36%
  • Empty weight: 11,500 lb (5,216 kg)
  • Loaded weight: 16,700 lb (7,575 kg)
  • Max takeoff weight: 15,700 lb (7,120 kg)
  • Powerplant:Wright J65 turbojet
    • Dry thrust: 7,800 lbf (34.70 kN)
    • Thrust with afterburner: 10,300 lbf (45.82 kN)
Performance
Armament
  • Guns: 1 × M61 Vulcan 20 mm (.79 in) cannon (XF-104 083-1002 only)[1]