The Fouga CM.88 Gemeaux was a 1950s French engine test-bed aircraft produced by Fouga. An unusual aircraft, it was two aircraft joined by a common wing.
| CM.88 Gemeaux | |
|---|---|
| Role | Engine test-bed |
| National origin | France |
| Manufacturer | Fouga |
| First flight | 1951 |
| Number built | 1 |
| Developed from | Fouga CM.8 |
Design and development edit
To meet a requirement to use as an engined testbed for Turbomeca turbojets, Fouga combined two CM.8 fuselages. It used the port and starboard outerwings with a new wing centre section to join the two fuselages. The V-tails fitted to each fuselage were joined at the top in a W configuration. The type was designated the Fouga CM.88-R Gemeaux I and first flew 6 March 1951, it was fitted with two Turbomeca Piméné turbojets, one on top of each fuselage. Further variants were produced as the engine fit was changed.
Variants edit
- Gemeaux I
- Original configuration with two 220 lb (100 kg) Turbomeca Piméné turbojet engines, first flown 6 March 1951.
- Gemeaux II
- Designation when powered by one 606 lb (275 kg) Turbomeca Marboré I turbojet engine, first flown 16 June 1951.
- Gemeaux III
- Designation when powered by one prototype 772 lb (350 kg) thrust Turbomeca Marboré II turbojet engine and first flown on 24 August 1951. A production version of the engine with 882 lb (400 kg) thrust was flown on 2 January 1952.
- Gemeaux IV
- Designation when powered by one 441 lb (200 kg) thrust Turbomeca Aspin I turbofan engine, first flown on 6 November 1951.
- Gemeaux V
- Final designation when powered by one 794 lb (360 kg) thrust Turbomeca Aspin II turbofan engine, first flown on 21 June 1952.
Specifications (Gemeaux III) edit
Data from [citation needed]
General characteristics
- Crew: 1
- Length: 6.66 m (21 ft 10 in)
- Wingspan: 10.76 m (35 ft 4 in)
- Height: 1.93 m (6 ft 4 in)
- Wing area: 12.8 m2 (138 sq ft)
- Airfoil: root: NACA 23014; tip: NACA 23012[1]
- Empty weight: 890 kg (1,962 lb)
- Max takeoff weight: 1,170 kg (2,579 lb)
- Powerplant: 1 × Turbomeca Marboré II turbojet engine, 3.92 kN (882 lbf) thrust
Performance
- Maximum speed: 249 km/h (155 mph, 134 kn)
- Service ceiling: 10,000 m (33,000 ft)
See also edit
Related lists
References edit
- ^ Lednicer, David. "The Incomplete Guide to Airfoil Usage". m-selig.ae.illinois.edu. Retrieved 16 April 2019.
- The Illustrated Encyclopedia of Aircraft (Part Work 1982-1985). Orbis Publishing.