(Northrop) F-89 Scorpion @·AIRCRAFTUBE

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Northrop F-89 Scorpion

The Northrop F-89 Scorpion was an early American jet-powered fighter designed from the outset as an all-weather interceptor, the first jet-powered aircraft designed as such. Though its straight wings limited its performance, it was among the first United States Air Force (USAF) jet fighters with guided missiles, and notably the first combat aircraft armed with air-to-air nuclear weapons (the unguided Genie rocket).

Design and development

The Scorpion stemmed from a United States Army Air Forces (USAAF) Air Technical Service Command specification ("Military Characteristics for All-Weather Fighting Aircraft") for a night fighter to replace the P-61 Black Widow. The preliminary specification, sent to aircraft manufacturers on 28 August 1945, required two engines and an armament of six guns, either .60-caliber (15 mm) machine guns or 20-millimeter (0.79 in) autocannon. The revised specification was issued on 23 November; it did not specify jet propulsion, but the desired maximum speed of 530 miles per hour (850 km/h) virtually dictated that all the submissions would be jet powered. The aircraft was to be armed with aerial rockets stored internally and six guns split between two flexible mounts, four guns forward and two in the rear. Each mount had to be capable of 15° of movement from the longitudinal axis of the aircraft. Each mount's guns were to be automatically controlled by radar. For ground attack, it had to be capable of carrying 1,000-pound (450 kg) bombs and to be able to carry a minimum of eight rockets externally. Bell Aircraft, Consolidated-Vultee, Douglas Aircraft, Goodyear, Northrop and Curtiss-Wright all submitted proposals. In March 1946, the USAAF selected the Curtiss-Wright XP-87, adapted from their proposed XA-43 attack aircraft, and Northrop's N-24 design, one of four submitted by the company.

The N-24, designed by Jack Northrop, was a slim-bodied swept-wing aircraft with a two-man pressurized cockpit and conventional landing gear. To reduce drag the two Allison J35 turbojet engines were buried in the lower fuselage, directly behind their air intakes, and they exhausted underneath the rear fuselage. The horizontal stabilizer was mounted just above the junction of the vertical stabilizer with the fuselage and had some dihedral.

A contract for two aircraft, now designated the XP-89, and a full-scale mock-up was approved on 13 June, although construction of the mock-up had begun immediately after the USAAF announced that the N-24 had been selected. It was inspected on 25 September and the USAAF was not impressed. The inspectors believed that the radar operator needed to be moved forward, closer to the pilot, with both crewmen under a single canopy, the magnesium components of the wing replaced by aluminum, and the fuel stowage directly above the engines moved. Other changes had to be made as wind tunnel and other aerodynamic tests were conducted. The swept wings proved to be less satisfactory at low speeds and a thin, straight wing was selected instead. Delivery of the first prototype was scheduled for November 1947, 14 months after the inspection. The position of the horizontal stabilizer proved to unsatisfactory as it was affected by the engine exhaust and it would be "blanked-out" by airflow from the wing at high angles of attack. It was moved half-way up the tail, but its position flush with the leading edge of the vertical stabilizer proved cause extra drag through turbulence and reduced the effectiveness of the elevators and rudder. Moving the horizontal stabilizer forward solved the problem. Another major change occurred when USAAF revised its specification to delete the rear gun installation on 8 October. Another inspection of the mock-up was held on 17 December and the inspectors only suggested minor changes even though the fuselage fuel tanks were still above the engines. Northrop's efforts to protect the fuel tanks were considered sufficient as the only alternative was to redesign the entire aircraft.

The XP-89 had a thin, straight, mid-mounted wing and a crew of two, seated in tandem. The slim rear fuselage and the high-mounted horizontal stabilizer led Northrop employees calling it the Scorpion—a name later formally adopted by the Air Force. The intended armament of four 20 mm M-24 cannon in a small nose turret was not ready when the XP-89 was completed in 1948. Pending the availability of either of the two turrets under development, an interim six-gun fixed installation, with 200 rounds per gun, was designed for the underside of the nose. The thin wing had a aspect ratio of 9% and used a NACA 0009-64 section which was selected for its low drag at high speed and stability at low speeds. A further advantage of the straight wing was that it could accommodate heavy weights at the wingtips. The wing could not fit the circular-type ailerons used in the P-61, so Northrup used the "decelerons" designed for the unsuccessful XP-79 prototype. These were clamshell-style split ailerons which could be used as conventional ailerons, as dive brakes, or function as flaps as needed. All flying surfaces, the flaps and the landing gear were hydraulically powered. The thin wing dictated tall, thin, high-pressure (200 psi (1,379 kPa; 14 kgf/cm²) mainwheel tires while the low height of the fuselage required the use of dual wheels for the nose gear.

The terms of the initial contract were revised and formalized on 21 May 1947 with the price increased to $5,571,111. The delivery date of the first aircraft was scheduled 14 months (July 1948) from signing and the second 2 months after that. A month before the prototype made its first flight on 16 August 1948 at Muroc Army Air Field, the USAF changed its designation for fighter aircraft from 'P' to 'F'. The XF-89 was fitted with 4,000 lbf (17.8 kN) J-35-A-9 turbojets and proved to be seriously underpowered. Initial flights were made with conventional ailerons, decelerons not being installed until December.

Several months earlier the Air Force conducted a competitive evaluation of the three existing all-weather interceptor prototypes, the XF-87, the XF-89, and the US Navy's XF3D Skynight. The evaluators were qualified night-fighter pilots, radar operators, and experienced maintenance non-commissioned officers. The pilots were not impressed with any of the aircraft and recommended procurement of an interim aircraft that resulted in the development of the Lockheed F-94 Starfire from the training version of the Lockheed F-80 Shooting Star. The F-89 proved to be the fastest of the three contenders although it was in last place in cockpit arrangement and ease of maintenance. One pilot claimed that the XF-89 was the only real fighter and compared the XF-87 to a medium bomber and the XF3D to a trainer. The full Committee on Evaluation overruled those evaluators who preferred the Douglas design and selected the XF-89 as it had the greatest potential for development. The Air Force subsequently cancelled the production contract for the F-87 to free up money for the Scorpion.

By November 1949 the second aircraft was virtually complete, but the Air Force was concerned about the design's poor thrust-to-weight ratio and decided to implement a weight-reduction program as well as upgrading the engines to the more powerful J-33-A-21 fitted with an afterburner. Other major changes included the replacement of the nose gun turret by the Hughes-designed six-gun nose, AN/ARG-33 radar, and E-1 fire-control system, permanent wing-tip fuel tanks, and the ability to lower the complete engine for better maintenance access. The new nose added 3 feet (0.91 m) to the length of the aircraft. It was redesignated YF-89A to better reflect its role as a pre-production testbed to evaluate equipment and changes planned for the F-89A production aircraft. The aircraft was essentially complete by February 1950.

After repairs from a crash landing on 27 June 1949, the XF-89 was flown to March AFB to participate in the RKO movie Jet Pilot in February 1950. Shortly afterward, the aircraft crashed on 22 February, killing the observer, when flutter developed in the elevator and the subsequent vibrations caused the entire tail to break off. Construction of the production models was suspended until the reasons for the accident were discovered. Engineering and wind tunnel tests revealed that the geometry of the rear fuselage and the engine exhaust created flutter-inducing turbulence that was aggravated by the high-frequency acoustic energy from the exhaust. Fixes for the problem involved the addition of a "jet wake fairing" at the bottom rear of the fuselage between the engines, external ("ice tong") mass balances for the elevator, pending the design of internal mass balances, and the addition of exhaust deflectors to the fuselage to reduce the turbulence and the consequent flutter.

Well before the YF-89A was complete, a $39,011,622 contract was awarded to Northrop on 13 May 1949 for 48 F-89A aircraft, one static test airframe and the modifications made to the YF-89A.

Operational history

Production was authorized in January 1949, with the first production F-89A flying in September 1950. It had AN/APG-33 radar and an armament of six 20 mm (.79 in) T-31 cannons with 200 rpg. The swiveling nose turret was abandoned, and 300 US gal (1,100 l) fuel tanks were permanently fitted to the wingtips. Underwing racks could carry 16 5 in (127 mm) aerial rockets or up to 3,200 lb (1,455 kg) of bombs.

Only 18 F-89As were completed, which were mainly used for tests and trials, before the type was upgraded to F-89B standard, with new avionics. The type entered service with the 84th Fighter-Interceptor Squadron in June 1951. These had considerable problems with engines and other systems, and soon gave way to the F-89C. Despite repeated engine changes, problems persisted, compounded by the discovery of structural problems with the wings that led to the grounding of the F-89 and forced a refit of 194 -A, -B, and -C models.

The major production model was the F-89D, which first flew 23 October 1951 and entered service in 1954. It removed the cannon in favor of a new Hughes E-6 fire control system with AN/APG-40 radar and an AN/APA-84 computer. Armament was two pods of 52 2.75 in (70 mm) "Mighty Mouse" FFAR rockets, for a total of 104. A total of 682 were built.

Proposed re-engined F-89s, designated F-89E and F-89F, were not built, nor was a proposed F-89G that would have used Hughes MA-1 fire control and GAR-1/GAR-2 Falcon air-to-air missiles like the Convair F-106 Delta Dart.

The subsequent F-89H, which entered service in 1956, had an E-9 fire control system like that of the early F-102 and massive new wingtip pods each holding three Falcons (usually three semi-active radar homing GAR-1s and three infrared GAR-2s) and 21 FFARs, for a total of six missiles and 42 rockets. Problems with the fire control system delayed the -H's entry into service, by which time its performance was notably inferior to newer supersonic interceptors, so it was phased out of USAF service by 1959.

The final variant was the F-89J. This was based on the F-89D, but replaced the standard wingtip missile pod/tanks with 600 gal (2,271 l) fuel tanks and fitted a pylon under each wing for a single MB-1 Genie nuclear rocket (sometimes supplemented by up to four conventional Falcon air-to-air missiles). The F-89J became the only aircraft to fire a live Genie as the John Shot of Operation Plumbbob on 19 July 1957. There were no new-build F-89Js, but 350 -Ds were modified to this standard. They served with the Air Defense Command, later renamed the Aerospace Defense Command (ADC), through 1959 and with ADC-gained units of the Air National Guard through 1969. This version of the aircraft was extensively used within the Semi Automatic Ground Environment (SAGE) air defense system.

A total of 1,050 Scorpions of all variants were produced.

Variants

  • XF-89 : First prototype, powered by two 4,000 lbf (17.8 kN) Allison J-35-A-9 engines.
  • XF-89A : Second prototype. Fitted with more powerful (5,100 lbf (22.7 kN) dry, 6,800 lbf (30.3 kN) with reheat) J-35-A-21A engines and revised, pointed nose with cannon armament.
  • F-89A : First production version, eight built. Fitted with revised tailplane and six cannon armament.
  • DF-89A : F-89As converted into drone control aircraft.
  • F-89B : Second production version with upgraded avionics. 40 built.
  • DF-89B : F-89Bs converted into drone control aircraft.
  • F-89C : Third production version with more powerful engines (5,600 lbf (25.0 kN) dry, 7,400 lbf (32.0 kN) reheat J-35-A-21 or −33). 164 built.
  • YF-89D : Conversion of one F-89B to test new avionics and armament of F-89D.
  • F-89D : Main production version which saw deletion of the six 20 mm (.79 in) cannons in favor of 104 rockets in wing pods, installation of new Hughes E-6 fire control system, AN/APG-40 radar and the AN/APA-84 computer. This new system allowed the use of a lead-collision attack in place of the previous lead-pursuit-curve technique. A total of 682 built.
  • YF-89E : One off prototype to test the Allison YJ71-A-3 engine (7,000 lbf (31.2 kN) dry thrust, 9,500 lbf (42.4 kN) with reheat), converted from F-89C.
  • F-89F : Proposed version with new fuselage and wings and J71 engines, never built.
  • F-89G : Proposed version equipped with Hughes MA-1 fire control and GAR-1/GAR-2 Falcon air-to-air missiles, never built.
  • YF-89H : Modified F-89D to test features of F-89H. Three converted.
  • F-89H : Version with E-9 fire control system, six GAR-1/GAR-2 Falcon missiles and 42 Folding Fin Aircraft Rockets (FFAR). 156 built.
  • F-89J : Conversion of F-89D with underwing hardpoints for two MB-1 Genie nuclear armed rocket and four Falcon missiles, and carrying either the standard F-89D rocket/fuel pod or pure fuel tanks. A total of 350 were converted from F-89Ds.

Operators

United States :

  • United States Air Force
  • Air National Guard

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This text is available under the Creative Commons Attribution-ShareAlike License
Source : Article Northrop F-89 Scorpion of Wikipedia ( authors )

Specifications (F-89D)

  • Crew : 2.
  • Length : 53 ft 9½ in (16.40 m).
  • Height : 17 ft 6 in (5.33 m).
  • Wingspan : 59 ft 8½ in (18.20 m).
  • Wing area : 606 ft² (56.30 m²).
  • Empty weight : 25,194 lb (11,428 kg).
  • Loaded weight : 37,190 lb (16,869 kg).
  • Max. takeoff weight : 42,241 lb (19,161 kg).
  • Maximum speed : 635 mph (552 knots, 1,022 km/h) at 10,600 ft (3,200 m).
  • Ferry range : 1,366 mi (1,188 nm, 2,200 km).
  • Service ceiling : 49,200 ft (15,000 m).
  • Rate of climb : 7,440 ft/min (37.8 m/s).
  • Powerplant : Two Allison J35-A-35 afterburning turbojets.
  • Dry thrust : 5,440 lbf (24.26 kN) each.
  • Thrust with afterburner : 7,200 lbf (32.11 kN) each.
  • Armament :
    • 104× 2.75 in (70 mm) "Mighty Mouse" folding-fin aerial rockets.
    • 16× 5 in (127 mm) aerial rockets on underwing racks or
    • Bombs : 3,200 lb (1,500 kg).

— — — = = — — —

This text is available under the Creative Commons Attribution-ShareAlike License
Source : Article Northrop F-89 Scorpion of Wikipedia ( authors )
Northrop F-89 Scorpion : Your comments on this subject
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