Northrop-McDonnell Douglas YF-23

    The project to create advanced tactical fighter was conceived in the early years of the Reagan administration. The Commission had submitted a drawing of the future aircraft, which is fully able to meet the highest new requirements. Competitor is a company Lockheed aircraft with its YF-22.

    Fuselage YF-23A combines the requirements of low visibility, and high aerodynamic efficiency, providing a high coefficient of scattering radio beam. Plane YF-23A has a long and narrow fuselage compared to the YF-22A Lockheed. " Main supporting structure of fuselage, as measured from the stabilizer to the front of the cabin, about 2 meters longer than the plane YF-22A. Profile YF-23A similar profile of high-speed spy plane SR-71 Lockheed. "

    The nose of the aircraft is out of the cab, chassis, electronics and cover for the deployment of weapons. Fairing engine installed in aircraft YF-23 were larger than the production versions of the F-23, as they were designed for reverse thrust, provided for the earlier models of fighter planes, but then eliminated.

    Under the wings are trapezoidal air inlets, which eliminates the need for large additional ducts.Above each inlet has a valve to provide additional air flow to the engines during takeoff or flight at low speeds.

    Sock wing YF-23A is deployed back to 40 degrees and the rear edge of the wing deployed forward at the same angle. When looking at the airplane from the top you will notice that the wing is shaped like a triangle. Inside the wing fuel tanks are located.

    When you create a YF-23A aircraft firm Northrop decided to abandon the use of thrust vector control. This was done to preserve the low-mass, and to achieve the improvement of all characteristics of the aircraft invisible.

    Unlike an airplane YF-22A, YF-23A is not equipped with thrust vector control. The exhaust nozzles are located between the keels in the rear fuselage, and opening up. Above each nozzle has a regulatory valve. In order to reduce IR visibility nozzle covered with a special material to quickly dissipate heat.

    Stealth technology requirements also apply to an instrument that is placed entirely inside the plane. Load compartment holds up to 4 missiles AIM-120 air-to-air missiles. Before you gulp valve compartment open, breaking the full stealth aircraft on the radar screen. Planned to create a production model F-23 with a longer fuselage and an additional compartment for the two missiles AIM-9 "Saydvinder.

    The first YF-23A was delivered to the airbase Edwards June 22, 1990 YF-23A first flew from the airfield of Flight Test Center August 27, 1990, the aircraft was in the air for 20 minutes.In September of that year took 4 more flight of YF-23A.

    The second YF-23A (87-0801) with General Electric YF120 engines appeared on October 26 1990. Both YF-23 aircraft are in hangars at the air base Edwards, California. The project is now closed in favor of the F-22.

The program LRSA (Regional bomber) was planned to create an enlarged version of F-23 .

Tactical and technical characteristics of the YF-23 fighter jet:

Wingspan                                                                13.29 m

Aircraft length                                                           20.54 m

Aircraft height                                                             4.24 m

Area:

 wing of                                                                         87.8 m

 top view of 124.32 sq ft

 side view of 29.67 sq ft                         

 front view of 10.3 sq ft

equivalent volume of 37,998 cubic meters (more than the F-22 at 9.2%)

Weight, kg

         Avionics 858 kg ( F-22)

         zero fuel weight                      16,800 kg

         normal takeoff 26,516 kg (100% fuel + SD)

         Combat 22216 kg

         Takeoff Weight 29000 kg

         maximum take-off of about 40,000 kg (estimate)

         internal fuel 8600 kg (10,900 liters)

Load:

         normal 1,116 kg (6 + 2 SD)

         Maximum 10,370 kg

         FTB 8000 kg (?)

Engine Type                  2 turbofan Pratt & Whitney YF-119 (General Electric YF-120)

Static blast 2 x 15,810 kg

Maximum speed 1880 km / h

Cruising speed of 1,570 km / h

Practical ceiling 18000-20000 m

Combat radius 1300-1500 km

Runway length 915 m

Max g-load 6 g

Calculated vertical velocity at landing 3,05 m / s

Crew 1 person

Armament:

Built M61A1 gun (caliber 20 mm) can be installed up to eight SD air-to-air "AIM-120 and AIM-9L.

At external sites can be installed an existing conventional weapons.

normal weight F-23 :

            Fuel 100% 16800 + 8600 + 1116 = 26516 kg

Thrust 31620 / 26516 = 1.19

Wing loading 26,516 / 87.8 = 302 kg / m

Fuel 50% 16800 + 4300 + 1116 = 22216 kg

Thrust 31620 / 22216 = 1.42

Wing loading 22,216 / 87.8 = 253 kg / m

Fraternal site " ATF 1923 " on YF-23