Israeli Air Force Museum

Hatzerim Air Force Base
Beer Sheva
Israel

More info here at Israeli Air Force Museum

Australian National Aviation Museum

Corner of First Street and Second Avenue
Moorabbin Airport
Victoria, Australia

More info here at Australian National Aviation Museum

Classic Aircraft Aviation Museum

3005 NE Cornell Road
Hillsboro, OR 97125
United States of America

More info here at Classic Aircraft Aviation Museum

Sukhoi Su-27 Flanker

The Sukhoi Su-27 (NATO designation Flanker) is the front-line fighter aircraft designed by the Sukhoi Design Bureau.It is a twin-engined aircraft with a blended wing and fuselage, and twin tail fins. The aircraft were marketed at international air shows, putting up superb aerobatic displays, of  exceptional controllability at high angles of attack. Deliveries of the Su-27 fighters to the Soviet Air Force and Air Defence Forces started in 1985. Most of the series produced aircraft were T-10S design, hence the designation of Su-27S.

The first ‘Flanker-A’ prototypes flew on 20 May 1977. By the early 1980s, Sukhoi’s T10-1 prototype was the subject of much scrutiny by Western intelligence agencies, who dubbed it Flanker-A. As the prototype evolved into the Su-27 or Flanker-B production model, word of its potential as a fighter spread as well. Flanker-B Su-27S, which was the original version to enter service, entered service in 1984. The initial production single-seater was referred to as the Su-27S, allowing the designation Su-27 to refer to any or all variants in the family of aircraft

The aircraft has a near-zero static stability and thus require a fly-by-wire system. The SDU-10 pitch-only fly-by-wire system controls the pitch of the aircraft to ensure stability and controllability for the pilot, increase aerodynamic performance, limit overload and angle of attack when needed and decrease the airframe aerodynamic load.

The radar a powerful pulse-Doppler radar, and up to ten air-to-air missiles giving it a potent look-down shoot-down capability. The Flanker also features a rearward-facing radar at the end of a long boom placed between the engines allowing the Su-27 to search for targets behind the aircraft.

China also bought a license for the production of its own Su-27 fighters. Su-27SKs have since 1998 been produced as the F/J-11 in China under licence in accordance with intergovernmental agreement. The first licensed-production plane, assembled in the town of Shenyang, was flight tested on 16th December 1998.

Developing nation: Soviet Union/Russia.
Manufacturer/designer: Sukhoi Design Bureau.
Production line: IAPO Irkutsk Aviation Production Association, KNAAPO Komsomolsk-on-Amur Aviation Production Association, NAPO Novosibirsk Aviation Production Association.
Number built: 650+
Type aircraft: twin-engine fourth-generation Air Defence Fighter.
First flight: May 20 1977.
First delivery: 1984.

General characteristics

• Crew: 1 or 2
• Length: 21.9 m (72 ft)
• Wingspan: 14.7 m (48 ft 3 in)
• Height: 5.92 m (19 ft 6 in)
• Wing area: 62 m² (667 ft²)
• Empty weight: 16,380 kg (36,100 lb)
• Loaded weight: 23,430 kg (51,650 lb)
• Max takeoff weight: 30,450 kg (67,100 lb)
• Powerplant: 2× Saturn/Lyulka AL-31F turbofans, 122.8 kN (27,600 lbf) each

Performance

• Maximum speed: Mach 2.35 (2,500 km/h, 1,550 mph) at altitude
• Range: 3,530 km (2,070 mi) at altitude; (1,340 km / 800 mi at sea level)
• Service ceiling: 18,500 m (62,523 ft)
• Rate of climb: 300 m/s (64,000 ft/min)
• Wing loading: 371 kg/m² (76 lb/ft²)
• Thrust/weight: 1.09

Armament

• 1 × 30 mm GSh-30-1 cannon with 275 rounds
• 8,000 kg (17,600 lb) on 10 external pylons

• Up to 6 × medium-range AA missiles R-27, 2 × short-range heat-seeking AA missiles R-73
  • Upgraded Su-27SM is capable of using R-77 instead of R-27

Su-27S armament

• 30 mm GSH-30 Cannon, 150 rounds
• 6 × R-27R, R-27ER, R-27T, R-27ET
• 4 × R-73E
• FAB-250
• FAB-500
• B-8
• B-13
• S-24
• S-25

T-10 ‘Flanker-A’	Original prototype, sred from excessive drag, weak structure, excessive weight, and flutter; four built
T-10S	Redesigned prototype
P-42	Third Su-27S prototype (T10S-3) modified to set several climb and altitude records
T10-20R	Special conversion testbed used for long-range supersonic flight
Su-27 ‘Flanker-A’	Production model prototype and development aircraft; 15 built
Su-27S ‘Flanker-B’	First production model with refined aerodynamics and an aft radar extension, single-seat model designed for dual-role air defense and ground attack missions
Su-27SK	Export version of the Su-27S
Su-27SKM	Updated variant of the Su-27S for export
Su-27SM	Upgrade program for the Su-27S
Su-27P ‘Flanker-B’	Identical to the Su-27S but designed purely as an air defense interceptor and equipped with an in-flight refueling probe
Su-27UB ‘Flanker-C’	Two-seat combat-capable trainer with an improved radar in a longer nose
Su-27PU ‘Flanker-C’	Prototype of the Su-30 fighter bomber
Su-27K ‘Flanker-D’	Prototype of the Su-33 navalized fighter, also referred to as the T-10K
Su-27KU or Su-27IB	Prototype of the Su-34 bomber
Su-27M ‘Flanker-E’	Prototype of the Su-35 fighter
J-11	Chinese designation for the Su-27, perhaps up to 300 to be license built in China
J-11B	Improved version of the Su-27SK developed by China that features major upgrades including a new radar and an infrared search and track system while also incorporating Chinese weapons, reports suggest further orders for the Su-27SK (J-11) built in Russia are to be cancelled in favor of constructing the J-11B locally in China

Dassault Mirage 2000

The Aviation Marcel Dassault Mirage 2000C is an single engine, delta wing all weather night and day interceptor. Developed around 1973 as a successor of the Mirage III and Mirage V. The first of four single seat prototypes flew on March 10, 1978, and the fifth machine a private (Dassault) build  two-seater took the air in October 1980 as the precursor of the Mirage 2000B two-seat operational trainer.

The Mirage 2000N was derived from and looks much like the Mirage 2000B, but the Nuclear Strike variant includes stronger wings for low altitude operations, as well as low-level precision navigation-attack system, build around the Thomson-CSF Antilope 5 radar, with automated terrain following capability, at very high speed and very low altitude. The Mirage 2000N carries a single ASMP (nuclear weapon with 150 or 300 kilotons warhead) on a centerline pylon.

The old prototype of the Mirage 2000B was extensively modified to fly as the first next-generation Mirage 2000-5 in October 1990. The first single Mirage 2000-5 flew in may 1991.

The Mirage 2000-5 is a new version of the multi-role aircraft with a new avionics system:

New pilot/system interface.
Five displays ‘glass cockpit.
Head-Up/Level/Down and two Lateral.
RDY Multi-waveform pulse 12 Doppler radar.
Multi-target capability.
Multi-function radar.
New internal countermeasures system.
Multi-target firing and a new air-to-air MICA missile.

Developing nation: France.
Manufacturer/designer: Marcel Dassault Aviation.
Production line: Bordeaux-Mariagne.
Number built: 601
Type aircraft: multirole, single-engine fourth-generation jet fighter.
First flight: March 10, 1978
First delivery: November 1982 to Armée de L’Air

General characteristics Mirage 2000C

• Crew: 1
• Length: 14.36 m (47 ft 1 in)
• Wingspan: 9.13 m (29 ft)
• Height: 5.20 m (17 ft)
• Wing area: 41 m² (441.3 ft²)
• Empty weight: 24,541 kg  (54,100 lb)
• Max takeoff weight: 17,000 kg (37,500 lb)
• Powerplant: 1× SNECMA M53-P2 afterburning turbofan
• Dry thrust: 64.3 kN (14,500 lbf)
• Thrust with afterburner: 95.1 kN (21,400 lbf)

Performance

• Maximum speed: Mach 2.2 (2,333+ km/h, 1,450+ mph) at altitude/ 1,110 km/hr (690 mph) at low altitude
• Range: 1,550 km (837 nmi, 963 mi) with drop tanks
• Ferry range: 3,335 km (1,800 nmi, 2,073 mi) with auxiliary fuel
• Service ceiling: 17,060 m (59,000 ft)
• Rate of climb: 285 m/s (56,000 ft/min)
• Wing loading: 337 kg/m² (69 lb/ft²)
• Thrust/weight: 0.91

Armament

• Guns: 2× 30 mm (1.18 in) DEFA 554 revolver cannon, 125 rounds per gun
• Hardpoints: 9 total (4× under-wing, 5× under-fuselage) with a capacity of 6,300 kg (13,900 lb) external fuel and ordnance
• Rockets: Matra 68 mm unguided rocket pods, 18 rockets per pod
• Missiles:
  • Air-to-air missiles:
    • 6× MBDA MICA IR/RF
    • 2× Matra R550 Magic-II and 2× Matra Super 530D
  • Air-to-surface missiles:
    • 2× AM.39 Exocet
    • 2× AS-30L laser guided missile
    • 1× ASMP tactical nuclear cruise missile
• Bombs: 9× Mk.82

Avionics

• Thomson-CSF RDY (Radar Doppler Multi-target) radar

Fokker 100

Fokker’s largest aircraft, the Fokker 100 is a 100 seat jet airliner based on the F-28 Fellowship. Fokker 100 was certified by the United States Federal Aviation Administration as the Fokker 28-0100. The most noticeable difference was the much longer fuselage, which increased seating by 65% from 65 in the original F28 series to 107 in a three-by-two single-class arrangement. Fokker also introduced a redesigned wing for the 100, which they claimed was 30% more efficient in cruise. The engines were upgraded to the modern Rolls-Royce Tay turbofans, while the cockpit was updated with an all-glass instrumentation package (EFIS glass flightdeck). The Fokker 100 features twin fuselage-mounted engines and a T-tail.

Flightcrew of two. Max single class high density seating for 122. Standard single class seating for 107 at five abreast and 81cm (32in) pitch. Two class seating for 12 first class passengers at four abreast and 91cm (36in) pitch, and 85 economy class passengers; or 55 business class at five abreast and 86cm (34in) pitch, and 50 economy class pax.

Developing nation: Netherlands.
Manufacturer/designer: Fokker.
Production line: Amsterdam-Schiphol Airport  1986 – 1997
Type aircraft: Regional airliner.
First flight: November 30 1986, PH-MKH
First delivery: February 1989 to Swissair

General characteristics

• Capacity: 107 passengers
• Length: 35.53 m (116 ft 7 in)
• Wingspan: 28.08 m (92 ft 2 in)
• Height: 8.51 m (27 ft 11 in)
• Wing area: 93.5 m² (1,006 sq ft)
• Empty weight: 24,541 kg  (54,100 lb)
• Max takeoff weight: 45,810 kg (101,000 lb)
• Powerplant: 2 x Rolls-Royce Tay Mk 65015 turbofans, 15,100 lbf (67.2 kN) thrust each

Performance

• Maximum speed: 845 km/h (525 mph, 456 kn)
• Range: 3,070 km (1,970 mi; 1,710 nmi)
• Service ceiling: 10,700 m (35,105 ft)

Fokker 70

The Fokker 70 is a shortened development of the popular 100 seat class Fokker 100. Fokker began development of the new derivative airliner in November 1992 despite the absence of firm orders.

The first Fokker 70 was in fact the second Fokker 100 prototype which was modified by removing two fuselage plugs – one forward and one rear of the wing. Construction on this aircraft began in October 1992, first flight on April 4 1993. The first production Fokker 70 flew for the first time in July 1994 and certification was awarded on October 14 1994.

The last Fokker 70 was delivered in April 1997, when the production line closed following Fokker’s bankruptcy the previous year. Over the 70’s short production life, 47 were built.

Developing nation: Netherlands.
Manufacturer/designer: Fokker.
Production line: Amsterdam-Schiphol Airport 1993 – 1997.
Number built: 47.
Type aircraft: Regional airliner.
First flight: April 4 1993, PH-MKC.
First delivery: October 14 1994 to Ford Motor Company.

General characteristics

• Capacity: 80 passengers, 8,300 kg (18,300 lb)
• Length: 30.91 m (101 ft 5 in)
• Wingspan: 28.08 m (95 ft 5 in)
• Height: 8.51 m (27 ft 11 in)
• Wing area: 93.5 m² (1,006 sq ft)
• Empty weight: 22,673 kg (49,985 lb)
• Max takeoff weight: 38,100 kg (83,996 lb)
• Powerplant: 2 × Rolls-Royce Tay Mk.620 turbofans, 61.6 kN (13,800 lbf) thrust each

Performance

• Maximum speed: 743 km/h (462 mph; 401 kn)
• Maximum speed: Mach 0.75
• Range: 2,040 km (1,268 mi; 1,102 nmi)
• Service ceiling: 10,700 m (35,105 ft)