Fouga Magister

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The Fouga Magister was the world's first purpose-built two-seat turbojet-powered trainer aircraft.

1 Development
2 Variants
3 Specifications (CM.170-1)
4 Users
5 References
6 Related content

[edit] Development

In 1948, Fouga designed a jet-powered primary trainer called CM.130 for the French Air Force (Armée de l'Air, AdA) to replace piston-engined Morane-Saulnier MS.475 aircraft. When AdA found the aircraft lacking in power, Fouga enlarged the basic design and outfitted it with more powerful engines. The distinctive V-tail of the new CM.170 Magister originated on the CM.8 glider Fouga was using to experiment with jet engines. In 1950, AdA ordered 3 prototypes, with the first aircraft flying on July 23, 1952. The aircraft entered service with AdA in 1956. In addition to France, CM.170 were built under license by Valmet in Finland, Flugzeug Union Süd in Germany, and Israel Aircraft Industries in Israel, with a total of 918 built.

[edit] Variants

Fouga Magister

CM.170-1 Magister - first production version with Turbomeca Marbore II engines
CM.170-2 Magister - uprated Turbomeca Marbore IV engines with 4.7 kN (1,055 lbf) thrust each
CM.171 Makalu - enlarged airframe, Turbomeca Gabizo engines with 10.8 kN (2,422 lbf) thrust each, the only prototype lost in an accident on March 20, 1957
CM.173 Super Magister - Tubomeca Marbore Super VI engines with 5.1 kN (1,143 lbf) thrust each and ejection seats, one prototype built
CM.175 Zephyr - equipped with arrestor hook for French Navy
AMIT Fouga (Tzukit) - Israeli Air Force version, permanent weapon hardpoints under the wings for light attack capability
Fouga 90 - attempt to modernize the aircraft with Turbomeca Astafan engines with 7.6 kN (1,715 lbf) thrust each, reshaped canopy for better visibility, and upgraded avionics; failed to attract orders

[edit] Specifications (CM.170-1)

General characteristics

Crew: One or two
Length: 10.06 m (33 ft 0 in)
Wingspan: 12.15 m with wingtip fuel tanks (39 ft 10 in)
Height: 2.80 m (9 ft 2 in)
Wing area: 17.3 m² (186.1 ft²)
Empty weight: 2,150 kg (4,740 lb)
Loaded weight: 2,850 kg (6,280 lb)
Max takeoff weight: 3,200 kg (7,050 lb)
Powerplant: 2× Turbomeca Marbore IIA turbojets, 3.9 kN (875 lbf) each

Performance

Maximum speed: 715 km/h at 7,000 m (444 mph at 23,000 ft)
Range: 925 km (575 miles)
Service ceiling: 11,000 m (36,080 ft)
Rate of climb: 17 m/s (3,345 ft/min)
Wing loading: 165 kg/m² (34 lb/ft²)
Thrust/weight: 0.28

Armament

2x 7.5 mm or 7.62 mm machine guns, 200 rounds/gun
Up to 140 kg (310 lb) of weapons on 2 underwing hardpoints, including 50 kg (110 lb) bombs, unguided rockets, and Nord Aviation SS.11 anti-tank missiles.