Arado SC II

Arado SC II
Type:	Trainer aircraft
Design country:	German Empire
Manufacturer:	Arado
First flight:	1928
Commissioning:	1928
Production time:	1928-1930
Number of pieces:	10 (+ 1 SC-I conversion)

The Arado SC II is a German training aircraft developed in the 1920s and built in a smaller series by the Arado Flugzeugwerke in Warnemünde .

development

Like its predecessor, the SC I, the SC II was designed by Walter Rethel and appeared in 1928. Compared to its predecessor, it was kept somewhat larger in size and provided with a more powerful engine. The prototype was a converted SC I with the serial number 37 and the registration number D-1311 . During the acceptance flight on April 24, 1928 in Warnemünde it crash-landed in front of representatives of the DVL due to an engine failure, but could be repaired again. In 1928 an SC II was exhibited at the Paris Aérosalon and subsequently at the International Aviation Exhibition in Berlin. Ten aircraft had been built by 1930, the last of which was registered in January 1931, and eight of which were delivered to DVS and z. B. were flown to their schools in Berlin-Staaken and Schleissheim . An SC II was shipped to China in June 1930 and flown to Nanjing and Shanghai , what happened to it afterwards is uncertain. According to a former engineer from Arado, three more copies are said to have made it to China. The last two SC II were deleted from the register in June 1937.

construction

The SC II is a cantilever , heavily staggered one and a half decker in a composite construction . The fuselage consisted of a welded tubular steel frame with a rectangular cross-section, which ended in a vertical cutting edge. It was reinforced with diagonally welded steel tubes up to the rear seat and then reinforced with wire crossings. The engine mount and the front area were planked with aluminum sheets up to the front cabin and covered with fabric behind. The back of the fuselage was made from a detachable semicircular cover made of plywood, under which there was a luggage compartment with dimensions 75 × 60 × 40 cm that was accessible from the outside. The two crew cabins with double steering were located one behind the other and were open, in front of which there was a fire bulkhead with the 45-liter lubricant container. The water tank was installed above the engine, the NFK lamellar cooler underneath ("abdominal cooler").

The wings had a trapezoidal shape with rounded edge arches, with the lower wing slightly V-shaped. They were staggered and one-piece and consisted of a wooden frame with two box spars, belts and webs made of birch and half-timbered ribs made of plywood. The wing nose was made of plywood, as was the planking on the underside between the two spars, the rest was covered with fabric. The middle section of the upper wing, in which the fuel tank was housed, was designed as a canopy , supported on the lower wing connection by two struts. Two inclined N-stems were between the upper and lower wings. The connection of the lower wing to the fuselage was accomplished by four bolts on the lower longitudinal spar. Ailerons , consisting of a fabric-covered wooden frame, were only in the upper wing.

The tail unit consisted of fabric-covered tubular steel, the horizontal stabilizer was supported by I-struts towards the fuselage and the fin, and the elevator and rudder were balanced.

The landing gear of the SC II consisted of the main landing gear consisting of two spring struts with a split axle and a grinding spur at the rear. It was generally felt to be too weak for a trainer aircraft. The very short, rigid tail spur caused the aircraft to tilt on its side and break away on landing, which is why the SC II was probably not produced in large numbers.

Technical specifications

Parameter	Data
crew	2
span	above 13.20 m below 10.50 m
length	8.89 m
height	3.54 m
Wing area	39.98 m²
Preparation mass	1275 kg
Payload	710 kg
payload	70 kg
Takeoff mass	1985 kg
drive	a water-cooled six - cylinder four-stroke in - line engine with a rigid two-bladed wooden propeller (⌀ 3 m)
Type	BMW Va 5.5
Starting power continuous power	360 hp (265 kW) at 1650 rpm, 320 hp (235 kW) at 1580 rpm close to the ground
Fuel volume	600 l
Top speed	185 km / h near the ground 180 km / h at an altitude of 1000 m
Landing speed	80 km / h
Rate of climb	3 m / s
Rise time	5.39 min at 1000 m altitude
Service ceiling	5000 m

literature

• Volker Koos: Arado Flugzeugwerke 1925–1945 . Heel, Königswinter 2007, ISBN 978-3-89880-728-9 , pp. 17/18 .
• Jörg Armin Kranzhoff: Arado. History of an aircraft factory . Aviatic, Oberhaching 1995, ISBN 3-925505-27-X , p. 19/20 .
• Helmut Stützer: The German military aircraft 1919–1934 . E. S. Mittler & Sohn, Herford 1984, ISBN 3-8132-0184-8 , p. 56, 107 and 194 .