Military Users- Luftwaffe, Spanish Air Force, Czechoslovakian Air Force.
The Arado Ar 66 was a German single-engined, two-seat training biplane, developed in 1933.
It was also used for night ground-attack missions on the Eastern Front.
It was engineer Walter Rethel’s last design in collaboration with Arado, before Walter Blume, assigned as Arado Flugzeugwerke’s chief design engineer in 1933, took over the bulk of the Arado firm’s design duties.
Arado’s chief designer Walter Rethel started design of a new two-seat trainer in 1931, with the design being developed by Walter Blume when Rethel transferred to Messerschmitt, with the first prototype, the Ar 66a flying in 1932.
The Ar 66 had an Argus As 10 air-cooled inverted V8 engine producing about 179 kW (240 hp), which drove a 2.5 m (8.2 ft) two-blade propeller.
It carried 205 L (54 US gal) of fuel, and 17 L (4 US gal) of oil.
The fuselage had an oval cross-section and was made of welded steel tubes, covered with fabric.
The double wings provided very high lift, even at low speeds.
Both wings had the same span and an 8° sweep.
Construction consisted of a double pine wing spar structure, with lime tree ribs, and fabric covering.
There were ailerons in both the upper and lower wings.
The tail had a conventional design, with the horizontal stabilizers mounted on the fuselage upper edge. The rudder was placed behind the elevators.
Both the rudder and the elevators were of steel tube covered in fabric, and had a bigger surface than the first version to correct balance problems.
The steel tube undercarriage was attached to the fuselage in a “V” shape and used high-pressure rubber suspension.
The crew consisted of two: instructor pilot and trainee, seated in open tandem cockpits, equipped with dual controls.
The aircraft was equipped with instrument flight systems with photographic cameras were mounted as optional equipment.
Length: 8.3 m (27 ft 3 in)
Wingspan: 10 m (32 ft 10 in)
Height: 2.93 m (9 ft 7 in)
Wing area: 29.63 m2 (318.9 sq ft)
Aspect ratio: 6.2
Empty weight: 905 kg (1,995 lb)
Max takeoff weight: 1,330 kg (2,932 lb)
Fuel capacity: main tank:172 l (45 US gal; 38 imp gal); reserve tank:33 l (8.7 US gal; 7.3 imp gal); oil tank:17 l (4.5 US gal; 3.7 imp gal)
Power plant: 1 × Argus As 10C inverted V-8 air-cooled piston engine, 179 kW (240 hp)
Propellers: 2-bladed wooden fixed pitch propeller, 2.5 m (8 ft 2 in) diameter
Maximum speed: 210 km/h (130 mph, 110 kn) at sea level
Cruise speed: 175 km/h (109 mph, 94 kn) at optimum altitude
Landing Speed: 80 km/h (50 mph; 43 kn)
Range: 716 km (445 mi, 387 nmi)
Endurance: 4.1 hours
Service ceiling: 4,500 m (14,800 ft)
Rate of climb: 4.333 m/s (853.0 ft/min)
Time to altitude: 1,000 m (3,300 ft) in 4.1 minutes
Wing loading: 45 kg/m2 (9.2 lb/sq ft)
Power/mass: 7.44 kg/kW (12.24 lb/hp)
Fuel consumption: 26.7 l (7.1 US gal; 5.9 imp gal) / 100 km (62 mi)
Oil consumption: 0.86 l (0.23 US gal; 0.19 imp gal) / 100 km (62 mi)
2 kg (4.4 lb) and 4 kg (8.8 lb) anti-personnel bombs.
Jane’s Encyclopedia of Aviation-Michael J. H Taylor.
The Complete Book of Fighters-William Green & Gordon Swanborough.