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Arado
/ Arado Ar 66
Arado Ar 66
The Arado Ar 66 was a German single engine, two seat training biplane, developed in 1933.
It was also used for night ground attack missions on the Eastern Front.
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.
Specifications
Crew
Two
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 take-off 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)
Powerplant
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
Performance
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)
Armament
2 kg (4.4 lb)
&
4 kg (8.8 lb) anti personnel bombs.
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