Cessna 210

https://en.wikipedia.org/wiki/Cessna_210

The Cessna 210 Centurion is a six-seat, high-performance, retractable-gear,
single-engine, high-wing general aviation aircraft which was first flown in
January 1957 and produced by Cessna until 1985.

The early Cessna 210 (210 and 210A) had four seats with a Continental IO-470
engine of 260 hp (190 kW). It was essentially a Cessna 182B to which was added a
retractable landing gear, swept tail, and a new wing. In 1961 the fuselage and
wing were completely redesigned - the fuselage was made wider and deeper, and a
third side window was added. The wing planform remained the same (constant 64"
chord from centerline to 100 inches (2,500 mm) out, then straight taper to 44"
chord at 208 inches from centerline), but the semi-Fowler flaps (slotted,
rear-moving) were extended outboard, from Wing Station 100 to Wing Station 122,
which allowed a lower landing speed (FAA certification regulations state that a
single-engined aircraft must have a flaps-down, power-off stall speed no greater
than 70 miles/hour). To compensate for the reduced aileron span, the aileron
profile was changed and its chord enlarged. The 1964 model 210D introduced a 285
hp (213 kW) engine and two small child seats, set into the cavity which
contained the mainwheels aft of the passengers.

In 1967 the model 210G introduced a cantilever wing replacing the strut-braced
wing. Its planform changed to a constant taper from root chord to tip chord. In
1970 the 210K became the first full six-seat model. This was achieved by
replacing the flat leaf-springs used for the retractable main landing gear
struts (undercarriage) with tapered tubular steel struts of greater length. This
allowed the tires to be nested farther to the rear of the fuselage, making room
for the full-size rear seats. In 1979 the 210N model eliminated the folding
doors which previously covered the two retracted main wheels. The tubular spring
struts retract into shallow channels along the bottom of the fuselage and the
wheels fit snugly in closed depressions on the underside of the fuselage. Some
models featured de-icing boots as an option.

The aircraft was offered in a normally aspirated version, designated the model
210, as well as the turbocharged T210 and the pressurized P210 versions. The
Centurion II was an option introduced in 1970 with improved avionics, and was
available in both normally aspirated and turbocharged versions (Turbo Centurion
II)

Role
Light aircraft

National origin
United States

Manufacturer
Cessna

First flight
January 1957

Introduction
1957

Produced
1957-1986

Number built
9,240

Variants
Cessna 206

In November 2007, Cessna acquired the assets of Columbia Aircraft Company. The
Columbia 350 and 400 models were integrated into the Cessna single-engined range
and redesignated as the Cessna 350 and Cessna 400. These aircraft replaced the
Cessna 210 at the top end of the Cessna single-engined model line.

The Cessna 210 was manufactured in 26 model variants. The C210, C210A-D, the
Centurion C210E-H&J, Turbo Centurion T210F-H&J, the Centurion II C210K-N&R, the
Turbo Centurion II T210K-N&R and the P210N&R. The 210N, T210N (turbocharged),
and P210N (pressurized) versions were produced in the greatest quantity. The
rarest and most expensive models were the T210R and P210R, which were produced
only in small quantities in 1985-86.

Several modifications and optional fittings are also available including
different engine installations, wingtip tanks, speed brakes, STOL kits and gear
door modifications.

Specifications (T210N Turbo Centurion II)

General characteristics
Crew: One
Capacity: Five passengers
Length: 28 ft 2 in (8.59 m)
Wingspan: 36 ft 9 in (11.20 m)
Height: 9 ft 8 in (2.95 m)
Wing area: 175 ft² (16.23 m²)
Empty weight: 2,303 lb (1,045 kg)
Max. takeoff weight: 4,000 lb (1,814 kg)
Powerplant: 1 × Continental Motors TSIO-520-R air-cooled turbocharged flat-six,
310 hp (231 kW)

Performance
Maximum speed: 204 knots (235 mph, 378 km/h) at 17,000 ft (5,200 m)
Cruise speed: 193 knots (222 mph, 358 km/h) at 20,000 ft (6,100 m)
Stall speed: 58 knots (67 mph, 108 km/h) CAS, flaps down, power off
Range: 900 nmi (1,036 mi, 1,668 km) econ cruise at 10,000 ft (3,050 m)
Service ceiling: 27,000 ft (8,230 m)
Rate of climb: 930 ft/min (4.7 m/s)
Wing loading: 22.9 lb/ft² (111.8 kg/m²)
Power/mass: 0.078 hp/lb (0.13 kW/kg)




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