Credit
Rob Schleiffert · CC BY-SA 2.0 · Resized · CC BY-SA 2.0 · Source ↗ · Modified
FORCETALLY
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At a glance
Measured figures
Naval Super Frelon · overall, rotors turning
Single source23.03 m (75 ft 7 in) (overall, rotors turning)[source]
Configuration
| Specification | Aérospatiale SA 321 Super Frelon | Enstrom F-28 |
|---|---|---|
| Type | Transport helicopter[source] | Light helicopter[source] |
| National origin | France[source] | — |
| Manufacturer | Sud Aviation Aérospatiale[source] | Enstrom Helicopter Corporation[source] |
| Status | In service with the People's Liberation Army Naval Air Force[source] | — |
| Primary users | French Navy People's Liberation Army Air Force South African Air Force Iraqi Air Force |
F28F · Length
29 ft 3 in (8.92 m)[source]
Empty; Naval Super Frelon · Empty weight
Single sourceMaximum take-off; Naval Super Frelon · Max takeoff weight
Single source6,863 kg (15,130 lb)[source]
13,000 kg (28,660 lb)[source]
Empty; F28F · Empty weight
Single sourceMaximum take-off; F28F · Max takeoff weight
Single sourceNaval Super Frelon · 3 × Turboméca Turmo IIIC turboshafts (1,550 shp) each
Single source3 × Turboméca Turmo IIIC turboshafts , 1,160 kW (1,550 shp) each[source]
F28F · 1 × Lycoming HIO-360-F1AD four-cylinder, direct-drive, horizontally opposed, air-cooled, piston aircraft engine
Single source1 × Lycoming HIO-360-F1AD four-cylinder, direct-drive, horizontally opposed, air-cooled, piston aircraft engine, 225 hp (168 kW)[source]
Bars compare reported quantities only. A larger figure does not make a system better; configurations and test conditions differ.
| — |
| Number built | 110[source] | — |
|---|
| Manufactured | 1962–1981[source] | 1965-present[source] |
|---|
| Introduction date | 1966[source] | 1965[source] |
|---|
| First flight | 7 December 1962[source] | — |
|---|
| Developed from | SNCASE SE.3200 Frelon[source] | — |
|---|
| Developed into | Changhe Z-8[source] | Enstrom 480[source] |
|---|
| Capacity | 27 passengers or 15 stretchers[source] | two passengers[source] |
|---|
| Fuel capacity | 3,975 L (1,050 US gal; 874 imp gal) (normal)[source] | — |
|---|
| Fuselage length | 19.40 m (63 ft 8 in)[source] | — |
|---|
| Main rotor area | 280.6 m 2 (3,020 sq ft)[source] | 804 sq ft (74.7 m 2 ) NACA 0013.5[source] |
|---|
| Never exceed speed | 275 km/h (171 mph, 148 kn)[source] | — |
|---|
| Variants | — | Enstrom TH180 Spitfire Mark I[source] |
|---|
| Country of origin | — | Vereinigte Staaten[source]Country of design · Entwurfsland |
|---|