Saturday, June 11, 2005
Steve's Video Of The Day: Antonov AN-2 "Colt" In Action!
I love the designs that Russian aircraft designers come up with. The aircraft are so rugged! The Antonov "Colt" AN-2 fits the mould perfectly. She is powered by a 9 cylinder radial, PZL Kalisz ASZ-621R, which is a 1000 horsepower version of a Wright 1820 CI Cyclone engine, turning a 4 blade AW-2 propeller. This is basically the same configuration on the "Polish Otter". The AN-2 also has the distinction of being the aircraft of choice by people escaping the "Iron Curtain", as it transported more people to freedom than any other aircraft type, due to it's dependability and ability to operate from unimproved landing and take-off areas. A "ruggedly beautiful" ship, the Antonov "Colt"!
VIDEO - Antonov AN-2 "Colt" In Action!
(love it, sounds like a Polish Otter going by!)
VIDEO - AN-2 Short Field Take-Off!
AN-2 INFO:
A/C TYPE : Single-engined general purpose biplane.
WINGS: Unequal span single-bay biplane. Wing section RPS 14 per cent (constant). Dihedral, both wings, approx 2~ 48'. All-metal two-spar structure, fabric covered aft of front spar. I- type interplane struts. Differential ailerons and full span automatic leading-edge slots on upper wings, slotted trailing-edge flaps on both upper and lower wings. Flaps operated electrically, ailerons mechanically by cables and push/pull rods. Electrically operated trim tab in port aileron.
FUSELAGE : All-metal stressed skin semi-monocoque structure of circular section forward of cabin, rectangular in the cabin section and oval in the tail section.
TAIL UNIT : Braced metal structure. Fin integral with rear fuselage. Fabric covered tailplane. Elevators and rudder operated mechanically by cables and push/pull rods. Electrically operated trim tab in rudder and port elevator. LANDING GEAR: Non-retractable split axle type, with long stroke oleo shock absorbers. Mainwheel tyres size 800 x 260 mm, pressure 2.25 bars (32.7 lb/sq in). Pneumatic shoe brakes on main units. Fully castoring and self-centring PZL Krosno tailwheel, size 470 x 210, with electro-pneumatic lock. For rough field operation the oleo-pneumatic shock absorbers can be charged from a compressed air cylinder installed in the rear fuselage. Interchangeable ski landing gear available optionally.
POWER PLANT : One 746 kW (1000 hp) PZL Kalisz ASz-62IR nine-cylinder radial aircooled engine, driving an AW-2 four-blade variable-pitch metal propeller. Six fuel tanks in upper wings, with total capacity of 1200 litres (317 US gallons; 264 Imp gallons). Oil capacity 120 litres (31.7 US gallons; 26.4 Imp gallons).
ACCOMMODATION : Crew of two on flight deck, with access via passenger cabin. Standard accommodation for 12 passengers, in four rows of three with centre aisle. Two foldable seats for children in aisle between first and second rows, and infant's cradle at front of cabin on starboard side. Toilet at rear of cabin on starboard side. Overhead racks for up to 160 kg (352 lb) of baggage, with space for coats and additional 40 kg (88 lb) of baggage between rear pair of seats and toilet. Emergency exit on starboard side at rear. Walls of cabin are lined with glass-wool mats and inner facing of plywood to reduce internal noise level. Cabin floor is carpeted. Cabin heating and starboard windscreen de-icing by engine bleed air; port and centre windscreens are electrically de-iced. Cabin ventilation by ram air intakes on underside of top wings.
SYSTEMS: Compressed air cylinder, of 8 litres (0.28 cu ft) capacity, for pneumatic charging of shock absorbers and operation of tailwheel lock at 49 bars (711 lb/sq in) pressure and operation of mainwheel brakes at 9.80 bars (142 lb/sq in). Contents of cylinder are maintained by AK-50 P engine driven compressor, with AD-50 automatic relief device to prevent overpressure. DC electrical system is supplied with basic 27V power (and 36V or 115V where required) by an engine driven generator and a storage battery. CO_2 fire extinguishing system with automatic fire detector.
AVIONICS : Dual controls and blind-flying instrumentation standard. R-842 HF and RS-6102 or Baklan-5 VHF lightweight radio transceivers, RW-UM radio altimeter (A-037 from 1 April 1989), ARK-9 radio compass, MRP-56P marker beacon receiver, GIK-1 gyro compass, GPK-48 gyroscopic direction indicator and SPU-7 intercom.
PERFORMANCE (at AUW of 5250 kg; 11574 lb):
Max level speed at 1750 m (5740 ft).....
.....139 knots (258 km/h; 160 mph)
Econ cruising speed.................100 knots (185 km/h; 115 mph)
Min flying speed.......................49 knots (90 km/h; 56 mph)
T-O speed..............................43 knots (80 km/h; 50 mph)
Landing speed..........................46 knots (85 km/h; 53 mph)
Max rate of climb at S/L.......................210 m (689 ft)/min
Service ceiling.................................4400 m (14425 ft)
Time to 4400 m (14425 ft)..................................30 min
T-O run: hard runway...............................150 m (492 ft)
grass............................................170 m (558 ft)
T-O to 15 m (50 ft): hard runway..................475 m (1558 ft)
grass...........................................495 m (1624 ft)
Landing from 15 m (50 ft): hard runway............427 m (1401 ft)
grass...........................................432 m (1417 ft)
Landing run: hard runway...........................170 m (558 ft)
grass............................................185 m (607 ft)
Range at 1000 m (3280 ft) with 500 kg (1102 lb) payload..... .....485 nm (900 km; 560 miles)
Weight empty....................................3450 kg (7605 lb)
Max fuel weight..................................900 kg (1984 lb)
Max T-O weight.................................5500 kg (12125 lb)
Max landing weight.............................5250 kg (11574 lb)
Max zero-fuel weight...........................4800 kg (10582 lb)
Max wing loading....................76.82 kg/m{2} (15.7 lb/sq ft)
Max power loading........................7.38 kg/kW (12.13 lb/hp)
PHOTO -AN-2 Cockpit
Good AN-2 Article
VIDEO - Antonov AN-2 "Colt" In Action!
(love it, sounds like a Polish Otter going by!)
VIDEO - AN-2 Short Field Take-Off!
AN-2 INFO:
A/C TYPE : Single-engined general purpose biplane.
WINGS: Unequal span single-bay biplane. Wing section RPS 14 per cent (constant). Dihedral, both wings, approx 2~ 48'. All-metal two-spar structure, fabric covered aft of front spar. I- type interplane struts. Differential ailerons and full span automatic leading-edge slots on upper wings, slotted trailing-edge flaps on both upper and lower wings. Flaps operated electrically, ailerons mechanically by cables and push/pull rods. Electrically operated trim tab in port aileron.
FUSELAGE : All-metal stressed skin semi-monocoque structure of circular section forward of cabin, rectangular in the cabin section and oval in the tail section.
TAIL UNIT : Braced metal structure. Fin integral with rear fuselage. Fabric covered tailplane. Elevators and rudder operated mechanically by cables and push/pull rods. Electrically operated trim tab in rudder and port elevator. LANDING GEAR: Non-retractable split axle type, with long stroke oleo shock absorbers. Mainwheel tyres size 800 x 260 mm, pressure 2.25 bars (32.7 lb/sq in). Pneumatic shoe brakes on main units. Fully castoring and self-centring PZL Krosno tailwheel, size 470 x 210, with electro-pneumatic lock. For rough field operation the oleo-pneumatic shock absorbers can be charged from a compressed air cylinder installed in the rear fuselage. Interchangeable ski landing gear available optionally.
POWER PLANT : One 746 kW (1000 hp) PZL Kalisz ASz-62IR nine-cylinder radial aircooled engine, driving an AW-2 four-blade variable-pitch metal propeller. Six fuel tanks in upper wings, with total capacity of 1200 litres (317 US gallons; 264 Imp gallons). Oil capacity 120 litres (31.7 US gallons; 26.4 Imp gallons).
ACCOMMODATION : Crew of two on flight deck, with access via passenger cabin. Standard accommodation for 12 passengers, in four rows of three with centre aisle. Two foldable seats for children in aisle between first and second rows, and infant's cradle at front of cabin on starboard side. Toilet at rear of cabin on starboard side. Overhead racks for up to 160 kg (352 lb) of baggage, with space for coats and additional 40 kg (88 lb) of baggage between rear pair of seats and toilet. Emergency exit on starboard side at rear. Walls of cabin are lined with glass-wool mats and inner facing of plywood to reduce internal noise level. Cabin floor is carpeted. Cabin heating and starboard windscreen de-icing by engine bleed air; port and centre windscreens are electrically de-iced. Cabin ventilation by ram air intakes on underside of top wings.
SYSTEMS: Compressed air cylinder, of 8 litres (0.28 cu ft) capacity, for pneumatic charging of shock absorbers and operation of tailwheel lock at 49 bars (711 lb/sq in) pressure and operation of mainwheel brakes at 9.80 bars (142 lb/sq in). Contents of cylinder are maintained by AK-50 P engine driven compressor, with AD-50 automatic relief device to prevent overpressure. DC electrical system is supplied with basic 27V power (and 36V or 115V where required) by an engine driven generator and a storage battery. CO_2 fire extinguishing system with automatic fire detector.
AVIONICS : Dual controls and blind-flying instrumentation standard. R-842 HF and RS-6102 or Baklan-5 VHF lightweight radio transceivers, RW-UM radio altimeter (A-037 from 1 April 1989), ARK-9 radio compass, MRP-56P marker beacon receiver, GIK-1 gyro compass, GPK-48 gyroscopic direction indicator and SPU-7 intercom.
PERFORMANCE (at AUW of 5250 kg; 11574 lb):
Max level speed at 1750 m (5740 ft).....
.....139 knots (258 km/h; 160 mph)
Econ cruising speed.................100 knots (185 km/h; 115 mph)
Min flying speed.......................49 knots (90 km/h; 56 mph)
T-O speed..............................43 knots (80 km/h; 50 mph)
Landing speed..........................46 knots (85 km/h; 53 mph)
Max rate of climb at S/L.......................210 m (689 ft)/min
Service ceiling.................................4400 m (14425 ft)
Time to 4400 m (14425 ft)..................................30 min
T-O run: hard runway...............................150 m (492 ft)
grass............................................170 m (558 ft)
T-O to 15 m (50 ft): hard runway..................475 m (1558 ft)
grass...........................................495 m (1624 ft)
Landing from 15 m (50 ft): hard runway............427 m (1401 ft)
grass...........................................432 m (1417 ft)
Landing run: hard runway...........................170 m (558 ft)
grass............................................185 m (607 ft)
Range at 1000 m (3280 ft) with 500 kg (1102 lb) payload..... .....485 nm (900 km; 560 miles)
Weight empty....................................3450 kg (7605 lb)
Max fuel weight..................................900 kg (1984 lb)
Max T-O weight.................................5500 kg (12125 lb)
Max landing weight.............................5250 kg (11574 lb)
Max zero-fuel weight...........................4800 kg (10582 lb)
Max wing loading....................76.82 kg/m{2} (15.7 lb/sq ft)
Max power loading........................7.38 kg/kW (12.13 lb/hp)
PHOTO -AN-2 Cockpit
Good AN-2 Article
