YAK 141 FREESTYLE, NEVER PRODUCED RUSSIAN SUPERSONIC VTOL

Yakoklev 141, NATO code named Freestyle. This innovative aircraft would have been the first supersonic VTOL fighter if it had reached Russian Navy service. Work began in 1975, but with budgetary and technical difficulties, particulary with the engine, delayed a first flight until March 1987, flown by Andrei Sinitsin.
The second prototype flew in April 1989, but crashed aboard the carrier Admiral Gorshkov in October 1991. During testing it several records for VTOL aircraft have created. Including a climbing speed record ( 116,5 seconds to 12,000 feet) and exactly his top speed to Mach 1,8.
For Russian aircraft, Yak 141 had more composites than other previous combat ones. There's up to 28% by weight being carbon fibre and remainder of the structure was mainly alumunium lithium alloys.
Development had virtually stopped by the time the Yak 141 appeared at the 1992 Farnborough Air Show. A land based STO/VL version was designed, but never developed. Now the surviving Yak 141 is in the Monino Air museum, Moscow. Russian was never being had the first operasional supersonic VTOL fighters. The US did finally wiyh his F35 JSF !
Yak 141 has a huge main vectored thrust turbofan engine assisted with 2 little lift turbofan only in Vertical take off or landing. That system finally has copied to F35 JSF when Yakoklev made some collaboration with Lockheed Martin. The partnership began in late 1991, though it was not publicly revealed by Yakovlev until 6 September 1992, and was not revealed by Lockheed-Martin until June 1994. Its swivelling main engine nozzle and automatic vertical Takeoff/landing assisted computer system have believed inspirating any F35 JSF aircraft programs.

Specifications (Yak-41)

General characteristics

• Crew: one: pilot
• Length: 18.36 m (60 ft 2 1/4 in)
• Wingspan: 10.105 m (33 ft 1 1/2 in)
• Height: 5.00 m (16 ft 5 in)
• Wing area: 31.7 m² (341 ft²)
• Empty weight: 11,650 kg (25,683 lb)
• Max takeoff weight: 19,500 kg (42,989 lb)
• Powerplant: 1× MNPK Soyuz R-79V-300 lift/cruise turbofan
  • Dry thrust: 108 kN (24,300 lbf)
  • Thrust with afterburner: 152 kN (34,170 lbf
• Lift engines: 2x RKBM RD-41 turbojets 41.7 kN (9,300 lbf) thrust each)

Performance

• Maximum speed: 1,800 km/h (1,118 mph, Mach 1.4+)
• Range: 2,100 km (1,305 mi)
• Ferry range: 3,000 km (1,865 mi)
• Service ceiling: 15,500 m (50,853 ft)
• Rate of climb: 15,000 m/min (49,213 ft/min)

Armament

• Guns: 1 × 30 mm GSh-301 cannon with 120 rounds
• Hardpoints: 4 underwing and 1 fuselage hardpoints with a capacity of 2,600 kg (5,733 lb) of external stores,with provisions to carry combinations of:
  • Missiles: R-73 Archer, R-77 Adder or R-27 Alamo air-to-air missiles
    
    

NORTHROP YF-23, NOT TO GOOD FOR BEAT F22

The Northrop/McDonnell Douglas YF-23 was an American prototype fighter aircraft designed for the United States Air Force. The YF-23 was entered in Advanced Tactical Fighter competition but lost out to the Lockheed YF-22, which entered production as the F-22 Raptor.
It's was a big shock to Northrop that have just cut off the contract of B-2 Spirit Stealth bomber !

Design and development

The YF-22 and YF-23 were competing in the USAF's Advanced Tactical Fighter (ATF) program, conceived in the early 1980s, to provide a replacement for the F-15 Eagle. Contracts for the two most promising designs were awarded in 1986.

The YF-23 was designed to meet USAF requirements for survivability, supersonic cruise (supercruise), stealth, and ease of maintenance. Designed with all-aspect stealth as a high priority, Northrop drew on the company's experience with the B-2 Spirit and F/A-18 Hornet. The YF-23 was an unconventional-looking aircraft with trapezoidal wings, substantial area-ruling, and a V-tail. Similar to the B-2, the exhaust from the YF-23's engines flows through troughs lined with heat ablating tiles, which shields the exhaust from infrared (IR) missile detection from below. The vehicle management system coordinates movements of the control surfaces for maneuvers and for stable flight, along with other aircraft functions. The wing flaps and ailerons deflect inversely on either side to provide roll. Pitch was provided by movement of both V-tails, and yaw was supplied but opposite movement. Deflecting the wing flaps down and ailerons up on both sides simultaneously provided for aerodynamic braking.

Although possessing an advanced design, in order to reduce costs and development, a number of F-15 Eagle components were utilized including the standard F-15 nose wheel unit and the forward cockpit of the F-15E Strike Eagle. Two aircraft were built. YF-23 #1 (PAV-1) was fitted with Pratt & Whitney YF119 engines, while YF-23 #2 (PAV-2) was fitted with General Electric YF120 engines. The YF-23 featured fixed nozzles. The first YF-23 was rolled out on 22 June 1990,^[5] and first flew on 27 August 1990. YF-23 #2 first flew on 26 October 1990.

The black YF-23 (PAV-1) was nicknamed "Black Widow II", after the Northrop P-61 Black Widow of World War II and had a red hourglass marking resembling the underbelly marking of the black widow spider. The black widow marking was briefly seen under PAV-1 before being removed at the insistence of Northrop management. The gray colored YF-23 (PAV-2) was nicknamed "Gray Ghost".

Evaluation

Both YF-23s were furnished in the configuration specified before the requirement for thrust reversing was dropped. The weapons bay was configured for weapons launch but no missiles were fired, unlike Lockheed's demonstration aircraft. The YF-23s flew 50 times for a total of 65.2 hours. The first YF-23 with P&W engines supercruised at Mach 1.43 on 18 September 1990 and the second YF-23 with GE engines reached Mach 1.6 on 29 November 1990. For comparison, the YF-22 achieved Mach 1.58 in supercruise. The flight testing demonstrated Northrop's predicted performance values for the YF-23.

The YF-22 won the competition in April 1991. The YF-23 design was more stealthy and faster, but the YF-22 was more agile. It has been speculated in the aviation press that the YF-22 was also seen as more adaptable to the Navy's Navalized Advanced Tactical Fighter (NATF), though as it turned out the US Navy abandoned NATF a few months later.

After losing the competition, both YF-23s were transferred to NASA's Dryden Flight Research Center, at Edwards AFB, California without the engines. NASA planned to use one of the aircraft to study strain gauge loads calibration techniques, but this did not occur.

Possible revival

In late 2004, Northrop Grumman proposed a YF-23 based design for the USAF's interim bomber requirement, a role for which the FB-22 and B-1R are also competing.Aircraft PAV-2 was modified by Northrop as a full size model of its proposed interim bomber. The interim bomber requirement has since been canceled in favor of a more long-term, bomber replacement requirement. The same YF-23-derived design could possibly be adapted to fulfill this role as well. However, it appears the possibility of a YF-23-based interim bomber was ended with the 2006 Quadrennial Defense Review, in lieu of a long range bomber with a much greater range.

Survivors

Both airframes remained in storage until mid-1996, when the aircraft were transferred to museums.

• YF-23A PAV-1 (s/n 87-0800) is now on display at the National Museum of the United States Air Force in Dayton, Ohio. The aircraft was recently put on display following restoration and is located in the Museum's Research and Development hangar.

• Aircraft PAV-2 was on exhibit at the Western Museum of Flight in Hawthorne, California. In 2004, it was loaned to Northrop Grumman and used for display purposes.Eventually, the aircraft will return to the museum's new location at Torrance Airport, Torrance, CA.

Specifications (YF-23)

General characteristics

• Crew: 1 (pilot)
• Length: 67 ft 5 in (20.60 m)
• Wingspan: 43 ft 7 in (13.30 m)
• Height: 13 ft 11 in (4.30 m)
• Wing area: 900 ft² (88 m²)
• Empty weight: 29,000 lb (14,970 kg)
• Loaded weight: 51,320 lb (23,327 kg)
• Max takeoff weight: 62,000 lb (29,000 kg)
• Powerplant: 2× General Electric YF120 or Pratt & Whitney YF119 , 35,000 lbf (156 kN) each

Performance

• Maximum speed: Mach 2.2+ (1,650+ mph, 2,655+ km/h) at altitude
• Cruise speed: Mach 1.6 (1,060 mph, 1,706 km/h) supercruise at altitude
• Range: over 2,790 mi (over 4,500 km)
• Combat radius: 865-920 mi (750-800 nmi, 1,380-1480 km)
• Service ceiling: 65,000 ft (19,800 m)
• Wing loading: 54 lb/ft² (265 kg/m²)
• Thrust/weight: 1.36

Armament

• 1 × 20 mm (.79 in) M61 Vulcan cannon
• 4-6 × AIM-120 AMRAAM or AIM-7 Sparrow air-to-air missiles
• 4 × AIM-9 Sidewinder air-to-air missiles

(WIKIPEDIA)

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ATAS NAMA : ARISTOTELES WIRAWAN ADHIDARMA, ST

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BUKU-BUKU YANG DIPESAN.
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ATAU EMAIL KAMI DI : ARISWIRA@GMAIL.COM
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Sukhoi Su-9/11/13 (1946), aborted First Russian made Jetfighter

The Sukhoi Su-9, or Samolyet K (Russian: Aircraft K), was an early jet fighter aircraft built in the Soviet Union shortly after World War II. The Su-9 also served as the basis for the Su-11 (Samolyet LK) and Su-13 (Samolyet TK).
Unfortunelly for Sukhoi Bureau, some intrics from another Russian Airplane Bureau like Mikoyan-Gurevich and Yakoklev made this time Soviet Dictators, Joseph Stalin cancelled all Sukhoi design. that's might be a reason why was untill early 70's the Mikoyan-Gurevich jetfighter rulling over the Russian sky.

Design and development

Su-9

While it bore a superficial resemblance to the German Messerschmitt Me 262, the Su-9 was not directly related to that aircraft. The first flight took place on 13 November 1946 and trials the following month proved promising.^[1] Su-9 was an advanced design for the time with an ejection seat and a provision for JATO rockets (2x 11.27 kN/2,530 lbf thrust for 8 seconds).^[1]

For the first time on a Soviet aircraft, the Su-9 utilized a brake parachute and unique wing-mounted air brakes. These were mounted between the ailerons and the engine nacelles and split above and below the wing.^[1] The aircraft was revealed to the general public on 3 August 1947 at the Tushino Airfield.^[2]

Development of the Su-9 was hampered by the stigma associated with its resemblance to the Me 262. Competing aircraft designer Aleksandr Yakovlev played this fact against Sukhoi with Joseph Stalin.^[2]

The Su-9 was abandoned in favor of the more advanced Su-11 (LK).

Su-11

Su-11 prototype, note much larger engines compared to Su-9

In early 1947, it was decided to modify the prototype two-seat Su-9 trainer then under construction. The resulting Su-11 (Samolet LK) was completed in May 1947. The most important modification was replacement of the German Jumo 004B engines with more powerful Soviet-designed Lyulka TR-1 turbojets developing 12.7 kN (2,865 lbf) thrust each. Su-11 thus became the first Soviet jet aircraft to use indigenous engines.^[1] Wing and fuselage structure had been revised to adapt to the considerably larger Lyulka engines. Su-11 first flew on 28 May 1947 with G.M. Shiyanov at the controls. Test flights revealed yaw instability at high speeds and the Lyulka engines were unreliable and eventually had been canceled. As the result, the project was abandoned in April 1948.^[1]

Su-13

Su-13 was the final attempt to further increase performance of the basic Su-9 design. The maximum wing thickness was reduced from 11% to 9% of the chord and the tailplanes were swept. The aircraft was also fitted with a pair of Klimov RD-500 (unlicensed Rolls-Royce Derwent copies) engines with 15.6 kN (3,500 lbf) thrust each.^[1] A night fighter version with radar and two 37 mm Nudelman N-37 cannon was also proposed. However, the projected top speed below 1,000 km/h (540 kn, 621 mph) was deemed insufficient and the project was abandoned before the prototype could be finished.

Operators

Soviet Union

• Soviet Air Force

Specifications (Su-9)

General characteristics

• Crew: One
• Length: 10.57 m (34 ft 8 in)
• Wingspan: 11.21 m (36 ft 9 in)
• Height: 3.72 m (12 ft 2 in)
• Wing area: 20.24 m² (217.87 ft²)
• Empty weight: 4,060 kg (8,950 lb)
• Loaded weight: 5,890 kg (12,990 lb)
• Max takeoff weight: 6,380 kg (14,070 lb)
• Powerplant: 2× Tumansky RD-10 turbojets, 8.8 kN (1,984 lbf) each
• *Fuel capacity: 1,750 kg (3,860 lb)

Performance

• Maximum speed: 885 km/h (480 kn, 550 mph) at 5,000 m (16,405 ft)
• Range: 1,140 km (615 nmi, 710 mi)
• Service ceiling: 12,800 m (41,984 ft)
• Rate of climb: 4.2 min to 5,000 m (16,405 ft)
• Wing loading: 291 kg/m² (60 lb/ft²)
• Thrust/weight: 0.31
• Endurance: 1 hour 44 minutes

Armament

• 1 × 37 mm Nudelman N-37 cannon with 30 rounds (1 × 45 mm Nudelman N-45 could be fitted instead)
• 2 × 23 mm Nudelman-Suranov NS-23 cannon with 200 rpg
• Up to 500 kg (1,102 lb) of bombs (1 × FAB-500 or 2 × FAB-250)

(wikipedia)