Fokker S.II / S.III / S.IV

Specifications

1st Flight 1922

S.IV

Crew: 2

Length: 8.55 m (28 ft 1 in)

Wingspan: 11.17 m (36 ft 8 in)

Height: 3.15 m (10 ft 4 in)

Wing area: 27.55 m2 (296.5 sq ft)

Empty weight: 650 kg (1,433 lb)

Gross weight: 1,000 kg (2,205 lb)

Powerplant: 1 × Le Rhône 9J 9-cylinder air-cooled rotary piston engine, 82 kW (110 hp)

Propellers: 2-bladed fixed pitch propeller

Performance

Maximum speed: 160 km/h (99 mph, 86 kn)

Stall speed: 65 km/h (40 mph, 35 kn)

Service ceiling: 4,000 m (13,000 ft)

Time to altitude: 1,000 m (3,300 ft) in 6 minutes

Wing loading: 36.29 kg/m2 (7.43 lb/sq ft)

Power/mass: 0.0830 kW/kg (0.0505 hp/lb)

Variants

The S.II was designed by Reinhold Platz as the second Fokker primary trainer, but unlike the earlier S.I monoplane the S.II was an unequal-span single-bay biplane with a fixed cross-axle landing gear.

It had side-by-side seating for an instructor and pupil and was originally powered by an 82 kW (110 hp) Thulin rotary engine.

The engine was later replaced with a Le Rhone-Oberursel engine.

S.III : Two-seat primary trainer biplane.

S-3 : One aircraft imported into the United States by Atlantic Aircraft.

The Fokker S.IV was a military trainer aircraft produced in the Netherlands in the mid-1920s.

It was a conventional, single-bay biplane with staggered wings of unequal span braced with N-struts, essentially a radial-engined development of the S.III.

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