Note: This information is from the YF-22 plastic model from Testor. Inside the model box was a packet, and this was the history that it said.

In 1981 the United States Air Force recognized the need for a modern air superority fighter to replace the F-15 and F-16 sometime in the middle 1990's. The study program was codenamed Senior Sky with the System Program Office(SPO) headed by USAF Col. Al Piccirillo. The future Advanced Technology Fighter(ATF) would use stealth, extreme maneuverability, and ability to go supersonic sans afterburner and the capabilities of long range and internal carriage of its weapons. 2 aircraft evolved for this contest: the Lockheed YF-22A and the Northrop YF-23A.

The YF-23 flew first on August 1990 with the YF-22A making its maiden flight on 29 September 1990. An intense flying competition followed and on 23 April 1991 it was announced the Lockheed airplane had won.

The test YF-22A had proved itself capable of supersonic flight without use of afterburner, termed "supercruise mode;" it proved capable of complete maneuver at extreme high angles of attack with complete control; it fired two different types of missiles and inflight refueling was a standard test procedure. With the Pratt & Whitney F-119 engines it flew to test requirement supercruise of Mach 1.43. The Production F-22A airplane will be even better and is expected to fly in late 1996.

DIMENSIONS AND EXTERNAL
      YF-22                                      13.11m
      F-22                                       13.56m
Length overall
      YF-22                                      19.56m
      F-22                                       18,92m
Height overall
      YF-22                                      6.41m
      F-22                                       5.05m

AREAS
Wings, gross
      YF-22 and F-22                             78.0m

WEIGHTS AND LOADINGS
Weight empty
      YF-22                                 over 13,608kg
       F-22                                    14,365kg
Max T-O weight
       F-22                                 almost 27,216kg

PERFORMANCE
Max level speed                            supercruise Mach 1.58
        with afterburning                   Mach 2.2 (1,451 mph)
Ceiling                                          15,240m
G limit+                                           +9
Max level speed at Sea Level                     800 knots

POWER PLANT
two Pratt&Whitney F-119-PW-100 turbofans
     (35,000 Ib. Class)

ARMAMENT
	AIM-120C AMRAAM radar-guided missiles
	AIM-9X Sidewinder heat-seeking missiles 
	M61A2 20ram cannon
	Mk. 83 1000 lb. bombs (JDAM guidance)

OTHERS
Thrust/Weight ratio:   1:1.2
Radar System: AN/APG-77
Defense System: AN/ALR-94 (integrated RWR and ECM)
Max. Altitude:             65,000 ft.
Max. Range            1,600 nautcal miles

Title
LOCKHEED MARTIN 645

US Air Force designation: F-22

Type

US Air Force next-generation tactical fighter, formerly known as Advanced Tactical Fighter (ATF) programme.

Lockheed teamed with General Dynamics (Fort Worth) and Boeing Military Airplanes to produce two YF-22 prototypes, civil registrations N22YF (with GE YF120) and N22YX (P&W YF119); USAF serial numbers 87-0700 and 87-0701 assigned, but only 87-0701 applied during second phase of testing, from late 1991. N22YF rolled out at Pahndale 29 August 1990; first flight/ferry to Edwards AFB 29 September 1990; first air refuelling (1 lth sortie) 26 October 1990; thrust vectoring in flight 15 November 1990; anti-spin parachute for high angle of attack tests on 34th to 43rd sorties; flight testing temporarily suspended 28 December 1990; 43 sorties/52 hours 48 minutes. N22YX first flight PalmdaleEdwards 30 October 1990; AIM-9M Sidewinder (28 November 1990) and AIM-120A AMRAAM (20 December 1990) launch demonstrations; achieved Mach 1.8 on 26 December 1990; temporarily grounded after 31 sorties/38 hours 48 minutes, 28 December 1990. Flight test demonstrations included 100°/s roll rate at 120 knots and supercruise flight in excess of Mach 1.58 without Second (F119-powered) YF-22 taken by road to Palmdale mid-1991; fitted with strain gauges; began further 100 hour test programme 30 October 1991; gathered data on aerodynamic loads, flight control aerodynamic effects, vibration/acoustic fatigue and maximum coefficient of lift; flown by 65 1 lth Test Squadron (F-22 Combined Test Force) of 65 10th Test Wing at Edwards AFB; non-fatal crash landing at Edwards 25 April 1992, following pilot-induced oscillations; total 100 hours 24 minutes in 70 flights since October 1990; non-flyable, but repaired for use as antenna testbed at Rome Air Development Center, Griffiss AFB, New York.

Fabrication of first component for first EMD aircraft (c/n 4001 ) began 8 December 1993 at Boeing's facility in Kent, Washington; assembly of forward fuselage launched at Marietta on 2 November 1995 with start of work on nose landing gear well; assembly work also begun at Fort Worth Summer 1995 with mating of three assemblies that comprise the mid-fuselage of first EMD aircraft taking place in Spring 1996, followed by road transfer of entire section to Marietta in August 1996 for start of final assembly process; first flight planned May 1997; low-rate production decision in August 1998; first production delivery August 2000; high-rate production decision due March 2002.

Highly integrated avionics for single pilot operation and rapid reaction. Radar, RWR and cornins/indent managed by single system presenting relevant data only, and with emissions controlled (passive to fully active) in stages, according to tactical situation. Common integrated processor (CIP) handles all avionics functions, including self-protection and radio, and automatically reconfigures to compensate for faults and failures. F-22 has two C[Ps, with space for third, linked by 400 Mbits{s fibre optic network (see Avionics).

Wing and horizontal tail leading-edge sweep 42° (both 48° on YF-22); trailingedge 17° forward, increased to 42° outboard of ailerons (straight trailing-edge on YF-22); all-moving five-edged horizontal tail (four-edged elements on YF-22). Vertical tail surfaces (22% larger on YF-22) canted outwards at 28°; leadingand trailing-edge sweep 22.9°; biconvex aerofoil. F-22's wing and stabilator areas same as YF-22, despite reprofiling. F-22 wing taper ratio 0.169; leading-edge anhedral 3.25°; root twist 0.5°; tip twist -3.1°; thickness/chord ratio 5.92 at root, 4.29 at tip; custom-designed aerofoil. Horizontal tails have no dihedral or twist.

Sidewinder AAMs stored internally in sides of intake ducts, with AMRAAMs, Sidewinders or GBU-32 JDAM 1000 precision-guided munitions in ventral weapons bay. Diamond-shaped cheek air intakes with highly contoured air ducts; intakes approximately 0.46m farther forward on YF-22; single-axis thrust vectoring included on PW119, but most specified performance achievable without.

Additional production F-22 changes from YF-22 include decreased wingroot thickness, modified camher and twist (increasing anhedral); all 48° plan angles changed to 42°; blunter nose; wheelbase reduced by approximately 0.46m; wheel track reduced by same; revised undercarriage legs and doors; constant chord ailerons; reprofiled cockpit canopy; dorsal airbrake deleted.

Menasco retractable tricycle type, stressed for no-flare landings of up to 3.05m/s. Nosewheel tyre 23.5 x 7.5-10; mainwheel tyres 37 x 11.5-18.

Comms: TRW communications/navigation/identification system, including Mk 12 IFE

Radar: Westinghouse/Texas Instruments AN/APG-77 electronically scanned radar (air-to-air and navigation).

Flight: TRW communications/navigation/identification subsystem; Litton inertial reference system.

Instrumentation: Fused situational awareness information is displayed to pilot via four Sanders/Kaiser colour liquid crystal multifunction displays (MFD); MFD bezel buttons provide pilot fortnat control.

Mission: Hughes common integrated processor (CIP); CIP also contains mission software that uses tailorable mission planning data for sensor emitter management and multisensor fusion; mission-specific information delivered to system through Fairchild data transfer equipment that also contains mass storage for default data and air vehicle operational flight programme; stores management system. General purpose processing capacity of CIP is rated at more than 700 million instructions per second (Mips) with growth to 2,000 Mips; signal processing capacity greater than 20 billion operations per second (Bops) with expansion capability to 50 Bops; CIP contains more than 300 Mbytes of memory with growth potential to 650 Mbytes. Intra-flight data link automatically shares tactical information between two or more F-22s. Airframe contains provisions for IRST and side-mounted phased-array radar.

Self-defense: Sanders/General Electric AN/ALR-94 electronic warfare (RF warning and countermeasures) subsystem.

Resources
-The YF-22 Model Booklet from Testor
-Jane's Fighter's Anthology Book Win95/98 game