1st Flight 1952
The Fouga CM.170 Magister is a 1950s French two-seat jet trainer aircraft.
Due to industrial mergers, the aircraft has been also known as the Potez CM.170 Magister, Sud Aviation CM.170 Magister and Aérospatiale CM.170 Magister, depending on where and when they were built.
Variants
CM.160
A proposed lightweight version of the CM.170R for operation from grass or makeshift runways.
CM.170 Magister
Three prototypes and 10 pre-production aircraft.
CM.170M Magister
Two prototypes for the French Aéronavale
CM.170R
Initial production version of the Magister.
CM.170-1 Magister
First production version with Turbomeca Marboré II engines, these were built in West Germany, Finland and Israel.
CM.170-2 Magister
Uprated Marboré VI 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 20 March 1957
CM.173 Super Magister/ Potez 94
Marboré Super VI engines with 5.1 kN (1,143 lbf) thrust each and ejection seats; one prototype built.
CM.175 Zéphyr
A shipboard trainer for the Aéronavale, with strengthened undercarriage, catapult attachments and arrestor hook.
Potez CM.191
4-seat version of the Magister; two prototypes built.
IAI Tzukit
or
AMIT Fouga – Israeli Air Force version, updated with new cockpit, composite materials
Fouga 90/90A
Development based on the CM.170 with Turbomeca Astafan engines with 7.6 kN (1,715 lbf) thrust each, reshaped canopy for better visibility, and upgraded avionics.
One prototype built.
Specifications
Crew: 2
Length: 10.06 m (33 ft 0 in)
Wingspan: 12.15 m (39 ft 10 in) (over tip tanks)
Height: 2.80 m (9 ft 2 in)
Wing area: 17.30 m2 (186.2 sq ft)
Aspect ratio: 7.42:1
Airfoil: NACA 64 Series
Empty weight: 2,150 kg (4,740 lb)
Gross weight: 2,850 kg (6,283 lb) (without tip tanks)
Max take-off weight: 3,200 kg (7,055 lb)
Fuel capacity: 730 L (190 US gal; 160 imp gal) internal fuel; 980 L (260 US gal; 220 imp gal) with tip tanks
Powerplant: 2 × Turbomeca Marboré IIA turbojets, 3.9 kN (880 lbf) thrust each
Performance
Maximum speed: 715 km/h (444 mph, 386 kn) at 30,000 ft (9,100 m)
Never exceed speed: 860 km/h (530 mph, 460 kn) (Mach 0.82)
Range: 1,200 km (750 mi, 650 nmi) (with external tanks)
Endurance: 2 hr 40 min (with external tanks)
Service ceiling: 11,000 m (36,000 ft)
Rate of climb: 16.99 m/s (3,345 ft/min) (without tip tanks)
Take-off distance to 15 m (50 ft): 930 m (3,050 ft)
Armament
2× 7.5 mm or 7.62 mm machine guns, 200 rounds/gun
Up to 140 kg (310 lb) of weapons on two under wing hard points, including 50 kg (110 lb) bombs, unguided rockets, and Nord Aviation SS.11 anti-tank missiles.
……………………………………………………………………………………………………………………………………………………………………………………………………………………………
