First flown in 1922, this two seat biplane was one of the first completely new products of the Fokker company after its post war move from Germany to Holland.
Stemming from the C.1 prototype, it was built with two sizes of wing, which could be exchanged in about an hour. The small wings were used on the C.IV A and DC.1 fighters and the large on the more numerous C.IV B, C and seaplane W. Some dozens were used by the Dutch and other air forces.
The prototype C.IV had a 400 hp Liberty engine. The C.IV was built as a successor to the C.I, being more spacious and able to transport more equipment. The C.IVA fighter-scout had less wing span, whilst the C.IVB and the C. IVC scouts had a greater span. Fokker manufactured 139 C.IVs and a number were also built in Spain.
The C.IV was a float-plane. The C.IV was a great success, and was used in America (where it was known as the CO-4), Argentine, Italy, Holland and the Dutch East Indies, Russia and Spain.
The C.IV was built in Madrid by Jorge Loring, under license from Fokker.

Span: 12.25 m (40 ft)
Length: 9.14 m (30 ft)
Gross weight: 1950 kg (4300 lb)
Maximum speed: 233 kph (146 mph).

The evaluation of three modified D XI fighters by the US Army Air Service prompted the design of the D XII tailored specifically to the USAAS specification. Designed from the outset for the 385hp V-1150 (Curtiss D-12) water-cooled engine and having fabric instead of plywood covered wings.
The D XII had no design commonality with the preceding D XI, but was of similar mixed construction and, initially, retained the sesquiplane configuration of its predecessor, the upper wing having some degree of leading-edge sweepback and overhung ailerons.

Flown for the first time on 21 August 1924, it was not accepted by the USAAC, as unsatisfactory characteristics displayed during initial trials necessitated major re-design, the sweepback being eliminated from the upper wing and a longer-span lower wing being introduced. Greater torsional rigidity was achieved by replacing the splayed V-type interplane struts with N-type struts and attaching these by single large-section struts to the top of the cabane strut system. At the same time, the small fixed tailfin was eliminated.
The D XII still proved unacceptable to the USAAS and further development was abandoned after three were built.

Engine: 385hp V-1150 (Curtiss D-12)
Max take-off weight: 1400 kg / 3086 lb
Empty weight: 998 kg / 2200 lb
Wingspan: 11.00 m / 36 ft 1 in
Length: 6.74 m / 22 ft 1 in
Height: 2.77 m / 9 ft 1 in
Wing area: 21.83 sq.m / 234.98 sq ft
Max. speed: 250 km/h / 155 mph
Cruise speed: 220 km/h / 137 mph
Range: 1100 km / 684 miles

The D.IX was used as the design basis for the D.XI, a single bay, unequal¬ span biplane of sesquiplane configuration. Powered by the 300 hp Hispano Suiza 8Fb eight-cylinder liquid-¬cooled engine of the D.IX, it was armed with two forward firing 7.92mm LMG 08/15 machine guns mounted in the engine cowling in front of the cockpit. The D XI had a fabric-covered steel-tube fuselage and plywood covered wooden wings and first flew on May 5, 1923.
One hundred and twenty-five were ordered by the Soviet government, and a further 50 were ordered on behalf of Germany’s Reichswehr by the financier Hugo Stinnes for the clandestine German air training centre, which, in 1924, was being established at Lipetsk, north of Voronezh, in the Soviet Union. In the event, the German order was cancelled and, in 1925, these 50 D XIs were sold to Romania.
At the beginning of 1924, three were supplied to the USAAC at McCook Field and tested as PW 7s with the 440 hp Curtiss D 12 (V-1150) engine. The first of these had standard plywood-covered wings with V-type interplane struts, and the second and third had fabric wing skinning and N-type strutting.
Two were supplied to Switzerland in 1925 for evaluation by that country’s Fliegertruppe.
A total of 177 D.XIs were built, the others going to the Argentine.

Span: 11.60 m (38 ft 0.75in)
Length: 7.00 m (22 ft 11.5in)
Height: 3.20 m / 10 ft 6 in
Wing area: 21.80 sq.m / 234.65 sq ft
Empty weight: 865 kg / 1907 lb
Gross weight: 1250 kg (2756 lb)
Maxi¬mum speed: 225 km/h (140 mph).
Range: 440 km / 273 miles

After the Armistice in 1918, Anthony Fokker returned to Holland and began to develop a new series of fighter designs originating from the D.VII of First World War. The first to appear, in prototype form only, was the D.IX, powered by a 300 hp Wright Hispano engine and was armed with two machine guns, flown for the first time in 1921, maximum speed was 220 kph. The prototype had a streamlined fuel tank built around the wheel axle, (like the C.I), but this tank was later removed upon delivery as PW 6 to the US Army Air Services. The sole prototype of the DI X was purchased for evaluation by the US Army Air Service and shipped to the USA in 1922, being assigned the designation PW-6. As evaluated by the USAAS, the aerofoil-section fuel tank was deleted, but the PW-6 was not considered to offer a sufficient advance over the D VII to warrant further development.
Of typical Fokker construction in employing a welded steel-tube fuselage and wooden wings each having two box spars, the D IX featured an aerofoil-shaped fuel tank between the main wheels as first tested by the V 36. Only one was built.
The D.IX was used as the design basis for the D.XI.

Max take-off weight: 1253 kg / 2762 lb
Empty weight: 874 kg / 1927 lb
Wingspan: 8.99 m / 29 ft 6 in
Length: 7.09 m / 23 ft 3 in
Height: 2.74 m / 8 ft 12 in
Wing area: 22 sq.m / 236.81 sq ft
Max. speed: 223 km/h / 139 mph
Cruise speed: 188 km/h / 117 mph
Range: 471 km / 293 miles

The Spanish C.III was a C.I with a Hispano Suiza engine. The C.IIIs were used for advanced training.