Republic XF-103
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| XF-103 Thunderwarrior | |
|---|---|
 Company artist's impression |
|
| Type | Interceptor |
| Manufacturer | Republic Aviation Company |
| Designed by | Alexander Kartveli and William O'Donnell |
| Status | Cancelled at mock-up stage |
| Unit cost | US$104 million for the program[1] |
The Republic XF-103 Thunderwarrior was an American project to develop a high speed interceptor aircraft to destroy Soviet bombers. Despite a prolonged development, it never progressed past the mock-up stage.
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[edit] Design and development
In 1949, the USAF issued a request for an advanced supersonic interceptor, known as the "1954 Interceptor" project, or Weapon System WS-201A. It called for a supersonic aircraft with all-weather capability, intercept radar and air-to-air missile armament. Republic was one of six companies to submit proposals. On 2 July 1951 three of the designs were selected, Convair's scaled-up XF-92, a Lockheed design and Republic's AP-57.
AP-57 was an extremely advanced design intended to be built almost entirely of titanium, capable of speeds up to Mach 3 at altitudes of at least 80,000 ft (24,400 m). To provide such performance, it was intended to have a Wright J67 turbojet (a license-built derivative of the Bristol Olympus engine) supplemented by an RJ55-W-1 ramjet. At "low" speeds the ramjet was turned off and the aircraft was powered by the J67 and its afterburner. At high speeds, starting above Mach 2, the jet engine would be shut down and the ramjet would be lit, utilizing a series of foldable, movable ramps allowing the air to go over the jet engine and directly into the ramjet. At full power, with both the jet engine in afterburner and ramjet, the engines provided nearly 40,000 lbf (180 kN) thrust in a 55,000 lb gross weight aircraft. Both engines were fed by a ventral Ferri intake, which featured a prominent, swept-forward lip, a design feature employed on the Republic RF-84F and later F-105.
All of the control surfaces were pure delta wings. The main wing was swept at 55 degrees, and could be rotated around the spar to provide variable incidence. For takeoff and landing, the wing was "tilted up" to increase the angle of attack while keeping the fuselage more horizontal. The system also allowed the fuselage to fly "flat" to the airflow at various speeds, setting the trim angle independent of the aircraft as a whole. This decreased trim drag and thereby improved range.
The wing was "cut" at about two-thirds of the span, the portion outside of this line able to rotate independently of the rest of the wing in order to act as large ailerons, or as Republic called them, "tiperons". In order to keep the surface areas in front and behind the pivot point somewhat similar, the "cut line" was closer to the fuselage in front of the pivot. Large conventional flaps ran from the fuselage to the tiperons.
The horizontal stabilizers were seemingly undersized, and mounted below the line of the wing. The larger vertical fin was supplemented by a ventral fin for high-speed stability, which folded to the right (as seen from behind) during takeoff and landing to avoid hitting the ground. Two "petal" style air brakes were mounted directly behind the horizontal surfaces, opening out and up at about a 45 degree angle into the gap between the horizontal and vertical surfaces. A provision for a braking parachute is not evident on the mock-up or the various artwork, although this was a common addition for aircraft of the era.
The fuselage was completely smooth, with a high fineness ratio for low drag at supersonic speeds. The design was developed prior to the discovery of the area rule, and does not display any of the "wasp waisting" common to aircraft primarily developed after 1952. The fuselage contours were mainly cylindrical, but blended into the intake starting around the wing root, giving it a rounded, rectangular profile through the middle, before reverting to a pure cylinder shape again at the engine nozzle.
The cockpit design originally featured a canopy, but low drag requirements for high speed required that the canopy be removed. A new design was proposed with the cockpit completely buried in the fuselage, with only two windows on the side for direct viewing, and a periscope providing forward visibility housed in a "mini canopy" on top. In 1955, the periscope concept was tested on a specially modified F-84G, which was flown on a long, cross-country flight with the pilot's forward vision blocked.[2][3] The XF-103 was not the only aircraft to use this sort of arrangement, as the Avro 730 used a very similar system.
A unique supersonic escape capsule (SEC) was designed for the XF-103. In an emergency the entire cockpit area would be ejected below the aircraft, along with a small portion of the fuselage that created a stable shape at high speeds. To enter and exit the aircraft, the ejection module was lowered on rails out of the bottom of the aircraft, allowing the pilot to simply walk into the seat, sit down, and raise the module. During an emergency, a shield stored in front of the seat would slide up into place in front of the pilot, sealing him into the SEC formed out of the shield and the seat back. Only the basic flight instruments were included in the "normal" cockpit area, most of the equipment was mounted around the pilot on the inside of the fuselage. The SEC was fully pressurized, allowing the pilot to continue operating the aircraft without a pressure suit when the capsule was "locked up".[4]
The entire nose of the aircraft was taken up by the large Hughes radar set, which offered (then) long detection ranges. Guidance and fire control were to be provided by the same MX-1179 package being developed for all of the WS-201 designs. Hughes had won this contract with their Hughes MA-1 fire control system, which was under development at the time. Weapons were carried in bays located on the sides of the fuselage behind the cockpit, which opened by flipping upward and thereby rotating the missiles out of their bays. It was to be armed with six GAR-1/GAR-3 Falcon (then known as MX-904), with a likely arrangement of three or four each GAR-1s and GAR-3s, fired in pairs (one each radar and infrared guided) to improve the odds of a hit. The XF-103 also was to feature 36 x 2.75-inch "Mighty Mouse" FFARs.
A full-scale mock-up was built and inspected in March 1953. A contract for three prototypes followed in June 1954.[2] Work on the prototypes was delayed by continued problems with the titanium construction, and more notably by continued problems with the engine. The contract was later reduced to a single prototype.[2] In the end, the J67 never entered production and the aircraft it had been chosen for were forced to turn to other engine designs, or were cancelled outright. Continuing delays and cost overruns caused the XF-103 program to be cut back to only one prototype. Republic suggested replacing the J67 with the Wright J65, a much less powerful engine, entirely unrealistic for an aircraft of this size.[citation needed] The project was eventually cancelled on 21 August 1957 with no flying prototypes ever being completed.[2]
[edit] Specifications (XF-103, as designed)
General characteristics
- Crew: one pilot
- Length: 77 ft (23.5 m)
- Wingspan: 34 ft 5 in (10.5 m)
- Height: 16 ft 7 in (5.1 m)
- Wing area: 401 ft² (37.2 m²)
- Empty weight: 24,949 lb (11,317 kg)
- Loaded weight: 38,505 lb (17,466 kg)
- Max takeoff weight: 42,864 lb (19,443 kg)
- Powerplant:
- 1× Wright XJ67-W-3 turbojet, 15,000 lbf (66.7 kN)
- 1× Wright XRJ55-W-1 ramjet, 18,800 lbf (83.6 kN)
Performance
- Maximum speed: Mach 3 (as a turbojet) / Mach 5 (ramjet-only)
- Service ceiling 80,000 ft + (24,390 m +)
- Rate of climb: 19,000 ft/min (5,800 m/min)
- Wing loading: 96 lb/ft² (470 kg/m²)
- Thrust/weight (jet): 0.57:1 (afterburner only); 0.95:1 (afterburner and ramjet)
- Combat radius: 245 mi (394 km)
- Ferry range: 1,545 mi (2,486 km)
Armament
- 36 × 2.75-in (70 mm) FFAR rockets
and
- 6 × GAR-1/GAR-3 AIM-4 Falcon
or
- 4 × GAR-1/GAR-3 AIM-4 Falcon missiles
- 2 × Nuclear-Tipped air-to-air missiles
[edit] See also
Comparable aircraft
[edit] References
[edit] Notes
- ^ Knaack, Marcelle Size. Encyclopedia of US Air Force Aircraft and Missile Systems: Volume 1 Post-World War II Fighters 1945-1973. Washington, DC: Office of Air Force History, 1978. ISBN 0-912799-59-5.
- ^ a b c d Republic XF-103, Joe Baugher
- ^ Jenkins 2004, p.23. The F-84G testbed (s/n 51-843) accumulated nearly 50 hours of flight testing with pilots reporting the periscope system worked extremely well.
- ^ Pace 1991, p. 128.
[edit] Bibliography
- Jenkins, Dennis R. "Titanium Titan: The Story of the XF-103." Airpower, January 2004.
- Pace, Steve. X-Fighters: USAF Experimental and Prototype Fighters, XP-59 to YF-23. Oscela, Wisconsin: Motorbooks International, 1991. ISBN 0-87938-540-5.
[edit] External links
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