Download - Military Transport Aircraft
COMPARATIVE
DATA SHEET
COMPILED BY
GROUP 5
G.DILLIKANNAN (200814012)
D. JOHN JEBARAJ (200814017)
ROHIT ANTONY DAVIS (200814029)
Military Transport Aircraft
1.The Antonov An-8
The Antonov An-8 is a twin-engined military transport aircraft by the Soviet design bureau OKB Antonov (today Antonov ASTC, Ukraine). The Antonov An-8 (NATO reporting name: Camp) is a Soviet-designed twin-turboprop-engine high-wing light military transport aircraft. Serving in the Soviet Air Force until the 1970s on front-line military duties, many were later transferred to Aeroflot for use as freighters and a few aircraft have been observed flying in Africa, particularly Liberia and Angola, despite Antonov having withdrawn the airworthiness certificate and support for the type in 2004, ending legal use of the aircraft.
In December 1951 OKB-153 initiated the design of a twin-engined assault transport aircraft, to be powered by two Kuznetsov TV-2 turboprop engines, and fitted with a large rear cargo door to allow vehicles to be driven straight into the hold. The resulting aircraft followed state of the art practice with a high wing carrying two propeller engines sat atop a rectangular section fuselage, tricycle undercarriage, with main gear units housed in pods either side of the fuselage, an upswept rear fuselage providing clearance of the tail unit for loading and unloading. After State acceptance trials production was not recommended due to poor spinning characteristics, directional stability and control issues, nosewheel shimmy, poor controllability when landing in crosswinds above 6 m/s (12 kt) and, last but not least, phugoid oscillations in all-three axes which were difficult to control and made piloting the prototype very tiring.
SPECIFICATIONS
Crew 6
Propulsion 2 Turboprop Engines
Engine Model Iwtschenko / Ivchenko / ZMKB Progress AI-20D
Engine Power (each) 3082 kW 4133 shp
Speed 520 km/h 281 kts 323 mph
Service Ceiling 9.600 m 31.496 ft
Range 3.900 km 2.106 NM 2.424 mi.
Empty Weight 24.400 kg 53.793 lbs
Max. Takeoff Weight 43.400 kg 95.680 lbs
Wing Span 37,00 m 121,4 ft
Wing Area 117,2 m² 1262 ft²
Length 30,70 m 100,7 ft
Height 9,70 m 31,8 ft
First Flight 11.02.1956
Production Status Out of production
Production Range 1957-1961
Total Production 151
3-D VIEW DIAGRAM
2. Boeing 367 C-97 Stratofreighter
Long-range military transport aircraft
The Boeing 367 C-97 Stratofreighter is a four-engine long-range military
transport and aerial tanker aircraft produced by the US-American manufacturer
Boeing Company. The Boeing C-97 Stratofreighter was a long range heavy
military cargo aircraft based on the B-29 bomber. Design work began in 1942,
with the prototype's first flight in 1944, and the production aircraft entering
service in 1947. Between 1947 and 1958, 888 C-97s in several variants were built
- 816 of them KC-97 tankers. C-97s served in the Berlin Airlift, the Korean War,
and the Vietnam War.
Some aircraft served as flying command posts for the Strategic Air
Command, while others were modified for use in Aerospace Rescue and Recovery
Squadrons (ARRS).The Boeing C-97 Stratofreighter was developed towards the
end of World War II by fitting an enlarged upper fuselage onto a lower fuselage
and wings which were essentially the same as the B-50 Super fortress with the
tail, wing, and engine layout being nearly identical. It was built before the death
of Boeing president, Philip G. Johnson. It can be easily distinguished from the 377
Stratocruiser airliners by the radar "beak" radome beneath the nose, and by the
flying boom and jets on later tanker models.
C-97s evacuated casualties during the Korean War. C-97s also participated
in the airlift of relief materials to Uli airstrip (Biafra) during the Nigerian Civil War.
Flying under the cover of darkness and at tree-level to evade radar, at least two
C-97s were lost. The USAF Strategic Air Command operated C-97 Stratofreighters
from 1949 through 1978.
SPECIFICATIONS Crew 5
Propulsion 4 Radial Engines
Engine Model Pratt & Whitney R-4360-59B Wasp Major
Engine Power (each) 2610 kW 3500 hp
Speed 604 km/h 326 kts 375 mph
Service Ceiling 9.205 m 30.200 ft
Range 6.919 km 3.736 NM 4.299 mi.
Empty Weight 37.421 kg 82.500 lbs
Max. Takeoff Weight 79.379 kg 175.000 lbs
Wing Span 43, 05 m 141,2 ft
Wing Area 164, 3 m² 1769 ft²
Length 33, 63 m 110,3 ft
Height 11, 66 m 38,3 ft
First Flight 15.11.1944
Production Status Out of production
Total Production 888
Developed from Boeing B-29 Super fortress
3-D VIEW DIAGRAM
3. C-74 Globe master I
Heavy Transport Aircraft
The Douglas C-74 Globe master I is a four-engine heavy military transport aircraft produced by the US-American manufacturer Douglas Aircraft Company in service with the United States Air Force (USAF).The Douglas C-74 Globemaster was a United States heavy-lift cargo aircraft built by the Douglas Aircraft Company in Long Beach, California.
Immediately after the United States became engaged in World War II, and particularly as a consequence of that nation's initial involvement against
Japanese forces in the Pacific, it was clear that transport aircraft would be of vital importance. Because of the theatre of operations envisaged, such aircraft would require both long range and great load-carrying capability, and in early 1942 Douglas began development of an aircraft to meet this requirement.
Designated Douglas C-74 Globemaster I, the first example of which 50 had been ordered by the US Army Air Force did not fly until 5 September 1945. It was a cantilever low-wing monoplane of all-metal construction, with a conventional tail unit, retractable tricycle landing gear with twin wheels on each unit, and power provided by four wing-mounted 2237kW Pratt & Whitney R-4360-27 radial engines. The C-74's large-capacity fuselage provided accommodation for the crew and 125 troops, or 115 stretchers with medical attendants, or up to 21840kg of cargo.
SPECIFICATIONS
Crew 4/5
Propulsion 4 Radial Engines
Engine Model Pratt & Whitney R-4360-27 Wasp Major
Engine Power (each) 2237 kW 3000 hp
Max. Cruise Speed 419 km/h 226 kts 260 mph
Max. Speed (vne) 502 km/h 271 kts 312 mph
Service Ceiling 9.144 m 30.000 ft
Range 12.549 km 6.776 NM 7.798 mi.
Empty Weight 39.087 kg 86.172 lbs
Max. Takeoff Weight 78.018 kg 172.000 lbs
Wing Span 52, 81 m 173, 3 ft
Wing Area 91, 7 m² 987 ft²
Length 37, 85 m 124,2 ft
Height 13, 34 m 43,8 ft
First Flight 05.09.1945
Production Status Out of production
Production Range 1945-1946
Total Production 14
Developed from Douglas DC-4
3-D VIEW DIAGRAM
4. C-124 Globe master II
Heavy Transport Aircraft
The Douglas C-124 Globe master II is a four-engine heavy military transport
aircraft produced by the US-American manufacturer Douglas Aircraft Company .
The C-124 was the primary heavy-lift transport for United States Air Force Military
Air Transport Service (MATS) during the 1950s and early 1960s until the C-141
Starlifter entered service. It served in MATS, later Military Airlift Command(MAC),
gained units of the Air Force Reserve and Air National Guard until 1974.
As a cargo hauler, it could carry tanks, guns, trucks and other heavy
equipment, while in its passenger-carrying role it could carry 200 fully equipped
troops on its double decks or 127 litter patients and their attendants. It was the
only aircraft of its time capable of transporting heavy equipment such as tanks
and bulldozers without prior disassembly.
The C-124 first flew on 27 November 1949, with the C-124A being delivered
from May, 1950. The C-124C was next, featuring more powerful engines, and an
APS-42 weather radar fitted in a "thimble"-like structure on the nose. Wingtip-
mounted combustion heaters were added to heat the cabin, and enable wing and
tail surface de-icing. The C-124As were later equipped with these improvements.
The C-124 was operational during the Korean War, and was also used to
assist supply operations for Operation Deep Freeze in Antarctica. They performed
heavy lift cargo operations for the US military worldwide, including flights to
Southeast Asia, Africa and elsewhere. From 1959 to 1961 they transported Thor
missiles across the Atlantic to England. The C-124 was also used extensively
during the Vietnam War transporting material from the U.S. to Vietnam.
SPECIFICATIONS
Crew 6
Propulsion 4 Radial Engines
Engine Model Pratt & Whitney R-4360-63A Wasp Major
Engine Power (each) 2834 kW 3800 hp
Speed 435 km/h 235 kts 270 mph
Service Ceiling 5.608 m 18.400 ft
Range 6.482 km 3.500 NM 4.028 mi.
Empty Weight 45.888 kg 101.166 lbs
Max. Takeoff Weight 88.224 kg 194.500 lbs
Wing Span 53,07 m 174,1 ft
Wing Area 232,8 m² 2506 ft²
Length 39, 75 m 130, 4 ft
Height 14, 72 m 48, 3 ft
First Flight 27.11.1949
Production Status Out of production
Total Production 447
Developed from Douglas C-74 Globemaster I
Data for (Version) Douglas C-124C Globemaster II
Variants C-124A, C-124C
3-D VIEW DIAGRAM
5. H.P.67 Hastings
Military Transport Aircraft
The Handley Page H.P.67 Hastings is a four-engine military transport aircraft produced by the British manufacturer Handley Page. The H.P.67 Hastings was operated by the Royal Air Force and the Royal New Zealand Air Force. The Handley Page H.P.67 Hastings was a British troop-carrier and freight transport
aircraft designed and built by Handley Page Aircraft Company for the Royal Air Force. At the time, it was the largest transport plane ever designed for the RAF, and it replaced the Avro York as the standard long-range transport.
It was an all-metal low-wing cantilever monoplane with conventional tail unit. It had all-metal tapering dihedral wings, which had been designed for the abandoned HP.66 bomber development of the Handley Page Halifax and a circular fuselage suitable for pressurisation up to 5.5 psi (38 kPa). It had a retractable undercarriage and tail wheel.
The Hastings was powered by four wing-mounted Bristol Hercules 101 sleeve valve radial engines. In service the aircraft was operated by a crew of five and could accommodate either 30 paratroopers, 32 stretchers and 28 sitting casualties, or 50 fully equipped troops. A total of 147 aircraft were built for the Royal Air Force and four for the Royal New Zealand Air Force, a total of 151.
SPECIFICATIONS
Crew 5-6
Propulsion 4 Radial Engines
Engine Model Bristol Hercules 106
Engine Power (each) 1249 kW 1675 hp
Speed 559 km/h 302 kts 348 mph
Service Ceiling 8.077 m 26.500 ft
Range 2.721 km 1.469 NM 1.690 mi.
Empty Weight 21.966 kg 48.427 lbs
Max. Takeoff Weight 36.287 kg 80.000 lbs
Wing Span 34, 44 m 113,0 ft
Wing Area 130, 8 m² 1408 ft²
Length 25, 20 m 82,7 ft
Height 6, 86 m 22,5 ft
First Flight 07.05.1946
Production Status Out of production
Total Production 151
Data for (Version) Handley Page Hastings C.Mk 2
Variants HP.67 Hastings C.1, C.1A, Met.1, C.2, C.3, C.4, T.5
3-D VIEW DIAGRAM
6. C-130 Hercules / L-100
Military Transport Aircraft
The Lockheed C-130 Hercules is a four-engine military transport aircraft
with a maximum payload of 19000 kg / 42000 lbs produced by the US-American
manufacturer Lockheed Corporation, today Lockheed Martin Aeronautics
Company. The Lockheed L-100 Hercules is the civilian variant. The C-130 is also
used as a gunship, for electronic warfare, search- and rescue, fire fighting, aerial
refuelling, maritime patrol and weather reconnaissance.
Capable of using unprepared runways for takeoffs and landings, the C-130
was originally designed as a troop, medical evacuation, and cargo transport
aircraft. The versatile airframe has found uses in a variety of other roles,
including as agunship (AC-130), for airborne assault, search and rescue, scientific
research support, weather reconnaissance, aerial refueling, maritime patrol and
aerial firefighting.
It is the main tactical airlifter for many military forces worldwide. Over 40
models and variants of the Hercules serve with more than 60 nations. The
Hercules holds the record for the largest and heaviest aircraft to land on an
aircraft carrier. During the 2003 invasion of Iraq (Operation Iraqi Freedom), the C-
130 Hercules has been used operationally by Australia, the UK and the United
States. After the initial invasion, C-130 operators as part of the Multinational force
in Iraq used their C-130s to support their forces in Iraq.
SPECIFICATIONS
Crew 3 (2)
Propulsion 4 Turboprop Engines
Engine Model Allison (Rolls-Royce) T56-A-15 (AE 2100D3)
Engine Power (each) 3362 (3460) Kw 4509 (4640) shp
Speed 650 (670) km/h 351 (362) kts 404 (417) mph
Max. Mach Mach 0.77
Service Ceiling 10.058 (8.534) m 33.000 (28.000) ft
Range 4.002 (5.250) km 2.161 (2.835) NM 2.487
(3.262) mi.
Empty Weight 37.648 (34.274) kg 83.000 (75.562) lbs
Max. Takeoff Weight 70.307 (79.379) kg 155.000 (175.000) lbs
Wing Span 40,41 m 132,6 ft
Wing Area 162,1 m² 1745 ft²
Length 29,79 m 97,7 ft
Height 11,61 m 38,1 ft
First Flight 23.08.1954
Production Status In production
3-D VIEW DIAGRAM
7. Transall C.160
Military Transport Aircraft
The Transall C.160 is a twin-engined military transport aircraft with a
maximum payload of 16000 kg / 35274 lbs. The Transall was developed by the
German/French joint-venture Transporter Allianz.
The Transall C-160 (often C.160) is a military transport aircraft developed
by a consortium of French and German aircraft manufacturers for the air forces of
those two nations and that of South Africa. The C-160 will be replaced in French
and German service by the Airbus A400M, now under development.[1]
The C-160 was originally conceived as a replacement for the French Air
Force's Nord Noratlas fleet. It is turboprop-powered and of conventional
configuration for aircraft of this type, with high wings, and a loading ramp built
into the rear of the fuselage. In size it falls between the Aeritalia G.222 and the C-
130 Hercules.
To replace the Transall, the Luftwaffe, the French Air Force, and the South
African Air Force ordered respectively 60.
SPECIFICATIONS
Crew 5
Propulsion 2 Turboprop Engines
Engine Model Rolls-Royce Tyne RTy.20 Mk.22
Engine Power (each) 4485 kW 6014 shp
Speed 513 km/h 277 kts 319 mph
Service Ceiling 8.230 m 27.000 ft
Rate of climb 396 m/min 1300 ft/min
Range 1.850 km 999 NM 1.150 mi.
Empty Weight 29.000 kg 63.934 lbs
max. Takeoff Weight 49.150 kg 108.357 lbs
Wing Span 40,00 m 131,2 ft
Wing Area 160,0 m² 1722 ft²
Length 32,40 m 106,3 ft
Height 12,36 m 40,6 ft
First Flight 25.02.1963
Production Status Out of production
Production Range 1965 - 1985
Total Production 210
3-D VIEW DIAGRAM
8. Airbus A400M
Military Transport Aircraft
The Airbus A400M is a multi-national four-engine turboprop military
transport aircraft. It was designed by Airbus Military as a tactical airlifter with
strategic capabilities. The aircraft's maiden flight, originally planned for 2008,
took place on 11 December 2009 in Seville, Spain.The A400M is undergoing flight
testing as of December 2010. Orders total 174 aircraft from 8 nations as of 2010.
The A400M is positioned as an intermediate size between the Lockheed C-
130, and the Boeing C-17 The Airbus A400M will increase the airlift capacity and
range compared with the aircraft it was originally set to replace, the older
versions of the Hercules and Transall. Cargo capacity is expected to double over
existing aircraft, both in payload and volume, and range is increased substantially
as well. The cargo box is 17.71 m long excluding ramp, 4.00 m wide, and 3.85 m
high. The height is 4.00 m aft of the wing and the ramp is 5.40 m long. he
A400M's wings are primarily carbon fibre reinforced plastic.
The Airbus A400M will operate in many configurations including cargo
transport, troop transport, Medical evacuation, aerial refuelling, and electronic
surveillance. The aircraft is intended for use on short, soft landing strips and for
long-range, cargo transport flights.
SPECIFICATIONS
Crew 3 or 4 (2 pilots, 3rd optional, 1 loadmaster)
Capacity 37,000 kg (82,000 lb)
Length 45.1 m (148 ft 0 in)
Wingspan 42.4 m (139 ft 1 in)
Height 14.7 m (48 ft 3 in)
Empty weight 76,500 kg (168,654 lb) operating weight [65]
Max takeoff weight 141,000 kg (310,852 lb)
Max. Landing Weight 122,000 kg (268,963 lb)
Total Internal Fuel 50,500 kg (111,330 lb)
Power plant 4 × Europrop TP400-D6[66] turboprop,
8,250 kW (11,060 hp) each
Propellers 8-bladed, 5.3 m (17 ft 5 in) diameter
Cruising speed 780 km/h (480 mph; 420 kn) (Mach 0.68 -
0.72)
Initial Cruise Altitude 9,000 m (29,000 ft)
Range 3,298 km (2,049 mi; 1,781 nmi) at max
payload
Range at 30-tonne payload 4,540 km (2,450 nmi)
Range at 20-tonne payload 6,390 km (3,450 nmi)
Ferry range 8,710 km (5,412 mi; 4,703 nmi)
Service ceiling 11,300 m (37,073 ft)
Tactical Takeoff Distance 980 m (3,215 ft )
Tactical Landing Distance 770 m (2,526 ft)
Turning Radius (Ground) 28.6 m
Characteristics
116 fully equipped troops / paratroops,
up to 66 stretchers accompanied by 25 medical personnel
3-D VIEW DIAGRAM
9. EADS CASA C-295
Military Transport Aircraft
The EADS CASA C-295 is a twin-turboprop tactical military transport aircraft
manufactured by Airbus Military in Spain.
The C-295 is a further development of the commercially successful
Spanish–Indonesian transport aircraft CASA CN-235 with a stretched fuselage,
50% more payload capability and new PW127G turboprop engines. The C-295
made its maiden flight in 1998. The first order came from the Spanish Air Force.
They are manufactured and assembled in the Airbus Military facilities in the
San Pablo Airport, in Seville, Spain. The C-295 is in service with the Armed Forces
of more than 10 countries. More than 80 C295s have been contracted. he C-295
was considered a higher risk by the Army due to its use of a new operational
mode to meet altitude and range requirements.
SPECIFICATIONS
Crew 2
Capacity 71 troops
Payload 9,250 kg (20,392 lbs)
Length 24.50 m (80 ft 3 in)
Wingspan 25.81 m (84 ft 8 in)
Height 8.60 m (28 ft 3 in)
Wing area 59 m² (634.8 ft²)
Loaded weight 9,250 kg (20,392 lbs)
Max takeoff weight 23,200 kg (51,146 lbs)
Power plant 2× Pratt & Whitney Canada PW127G
Maximum speed 576 km/h (311 knots, 358 mph)
Cruise speed 480 km/h (260 knots, 300 mph)
Range 4,300 km (2,600 mi) 2,300 nmi
Ferry range 5,220 km (3,240 mi; 2,820 nmi)
Service ceiling 7,620 m (25,000 ft)
Takeoff run 2,200 ft (670 m)
Landing run 1,050 ft (320 m)
3-D VIEW DIAGRAM
10. C-17 Globe master III
Heavy Military Transport Aircraft
The McDonnell Douglas / Boeing C-17 Globe master III is a heavy four-engined
military transport aircraft with a maximum payload of 77.519 kg (170.900 lbs)
produced by the US-American manufacturer Boeing (formerly McDonnell
Douglas).
Following the Vietnam War, the US Air Force realized the inadequacies of its
heavy-lift transport fleet and issued a requirement for a new design. While
intended to supplement and eventually replace the C-141 Star Lifter, this new C-
17 transport would need to combine the heavy load-lifting capability of the C-5
Galaxy with the ability of the C-130 Hercules to land close behind the front lines
on rough.
C-17 is used for rapid strategic airlift of troops and cargo to main operating
bases or forward operating bases throughout the world; it can also perform
tactical airlift, medical evacuation and airdrop missions. The C-17 carries the
name of two previous U.S. military cargo aircraft, the C-74 Globe master and the
C-124 Globemaster II.The aircraft requires a crew of three (pilot, co-pilot, and
loadmaster) for cargo operations. Cargo is loaded through a large aft door that
accommodates rolling stock, such as the 70-ton M1 Abrams tank, other armored
vehicles, trucks, trailers, etc., along with palletized cargo. The cargo
compartment is 88 feet (26.82 m) long by 18 feet (5.49 m) wide by 12 feet 4
inches (3.76 m) high. The cargo floor has rollers for palletized cargo that can be
flipped to provide a flat floor suitable for rolling stock.
The C-17 is designed to operate from runways as short as 3,500 ft (1,064 m) and
as narrow as 90 ft (27 m). In addition, the C-17 can operate from unpaved,
unimproved runways (although with greater chance of damage to the aircraft).
The thrust reversers can be used to back the aircraft and reverse direction on
narrow taxiways using a three- (or more) point turn.
SPECIFICATIONS
Crew 3
Propulsion 4 Turbofan Engines
Engine Model Pratt & Whitney F117-PW-100 (PW2040)
Engine Power (each) 179,7 kN 40400 lbf
Max. Cruise Speed 833 km/h 450 kts 518 mph
Max. Speed (vne) 959 km/h 518 kts 596 mph
Max. Mach Mach 0.77
Service Ceiling 13.716 m 45.000 ft
Range 4.482 km 2.420 NM 2.785 mi.
Empty Weight 122.015 kg 268.997 lbs
Max. Takeoff Weight 265.351 kg 585.000 lbs
Wing Span 51,76 m 169,8 ft
Wing Area 353,0 m² 3800 ft²
Length 53,04 m 174,0 ft
Height 16,79 m 55,1 ft
First Flight 15.09.1991
Production Status In production
3-D VIEW DIAGRAM
11. C-133 Cargo master
Heavy Military Transport Aircraft
The Douglas C-133 Cargomaster is a four-engine heavy military transport aircraft
produced by the US-American manufacturer Douglas Aircraft Company .
A high-mounted wing, external blister fairings on each side for the landing gear,
and rear-loading and side-loading doors ensured that access to, and the volume
of, the large cargo compartment were not compromised by these structures. The
cargo compartment (90 ft/27 m in length and 12 ft/3.7 m high) was pressurized,
heated, and ventilated.
The C-133 was for many years the only USAF aircraft capable of hauling very
large or very heavy cargo. By 1971, shortly before the introduction of the
Lockheed C-5 Galaxy, the Cargomaster was obsolete as well as being worn out,
and all were withdrawn from service in 1971. The C-133 was originally a 10,000-
hour airframe that had been life-extended to 19,000 hours. Severe vibration had
caused critical stress corrosion of the airframes to the point that the aircraft was
beyond economical operation any longer.
SPECIFICATIONS
Crew 6
Propulsion 4 Turboprop Engines
Engine Model Pratt & Whitney T34-P-9W
Engine Power (each) 5593 kW 7500 shp
Speed 578 km/h 312 kts 359 mph
Service Ceiling 9.144 m 30.000 ft
Range 6.438 km 3.476 NM 4.000 mi.
Empty Weight 54.550 kg 120.262 lbs
Max. Takeoff Weight 129.727 kg 286.000 lbs
Wing Span 54,77 m 179,7 ft
Wing Area 248,3 m² 2673 ft²
Length 48,02 m 157,5 ft
Height 14,71 m 48,3 ft
First Flight 23.04.1956
Production Status Out of production
Total Production 50
Data for (Version) Douglas C-133B Cargomaster
3-D VIEW DIAGRAM
12. C-5 Galaxy
Heavy Military Transport Aircraft
The Lockheed C-5 Galaxy is a four-engine heavy military transport aircraft
with a maximum payload of 122.472 kg (270.000 lbs) produced by the US-
American manufacturer Lockheed Corporation, today Lockheed Martin
Aeronautics Company.
The C-5 Galaxy is equipped with nose and tail cargo doors. The aircraft has
the ability to kneel down for easier loading. Cargo compartment of the C-5
Galaxy: height: 4,11m (13ft 5.8in), width: 5,79m (19ft), length: 43,8m (143ft
8.4in). The modernized C-5M Super Galaxy is powered by General Electric CF6-
80C2 engines (military designation F108-GE-100) with 225 kN (50580 lbs) of
thrust.
The Lockheed C-5 Galaxy is a large military transport aircraft built by
Lockheed. It was designed to provide strategic heavy airlift over intercontinental
distances and to carry outsize and oversize cargo. The C-5 Galaxy has been
operated by the United States Air Force (USAF) since 1969 and is one of the
largest military aircraft in the world.
The Galaxy is capable of carrying nearly every type of the Army's combat
equipment, including bulky items such as the 74 short tons (67 t) armored
vehicle launched bridge (AVLB), from the United States to any location on the
globe.
It has both nose and aft doors for "drive-through" loading and unloading of
cargo.
The C-5 features a cargo compartment 121 ft (37 m) long, 13.5 ft (4.1 m)
high, and 19 ft (5.8 m) wide, or just over 31,000 cu ft (880 m3).
SPECIFICATIONS
Crew 7
Propulsion 4 Turbofan Engines
Engine Model General Electric TF39-GE-1C
Engine Power (each) 191,4 kN 43035 lbf
Speed 919 km/h 496 kts 571 mph
Service Ceiling 10.363 m 34.000 ft
Range 4.445 km 2.400 NM 2.762 mi.
Empty Weight 169.645 kg 374.003 lbs
Max. Takeoff Weight 381.018 kg 840.001 lbs
Wing Span 67,88 m 222,7 ft
Wing Area 576,0 m² 6200 ft²
Length 75,51 m 247,7 ft
Height 19,85 m 65,1 ft
First Flight 30.06.1968
Production Status Out of production
Production Range 1968-1989
Total Production 131
3-D VIEW DIAGRAM
13. C-141 Starlifter
Military Transport Aircraft
The Lockheed C-141 Starlifter is a four-engine military transport aircraft
with a maximum payload of 41222 kg (90880 lbs) produced by the US-American
manufacturer Lockheed Corporation.
The Lockheed C-141 Starlifter is a military strategic airlifter in service with
the United States Air Force. Introduced to replace slower piston-engined cargo
planes such as the C-124 Globe master II, the C-141 was designed to a 1960
requirement and first flew in 1963; production deliveries of an eventual 248
began in 1965, and the aircraft is still in service almost 40 years later, although
the USAF plans to withdraw the C-141 from service in 2006 when sufficient C-17
Globe master III aircraft are available.
On 16 September 2004 the C-141 left service with active duty USAF units,
being confined to reserve units for the remainder of its service life. As of
September 25th, 2005, there are only 8 C-141 aircraft still flying (All from Wright-
Patterson AFB) near Dayton, Ohio.
SPECIFICATIONS
Crew 5-6
Propulsion 4 Turbofan Engines
Engine Model Pratt & Whitney TF33-P-7
Engine Power (each) 93,4 kN 21000 lbf
Speed 909 km/h 491 kts 565 mph
Max. Mach Mach 0.74
Service Ceiling 12.497 m 41.000 ft
Range 4.723 km 2.550 NM 2.934 mi.
Empty Weight 67.186 kg 148.120 lbs
Max. Takeoff Weight 155.582 kg 343.000 lbs
Wing Span 48,74 m 159,9 ft
Wing Area 299,9 m² 3228 ft²
Length 51,29 m 168,3 ft
Height 11,96 m 39,2 ft
First Flight 17.12.1963
Production Status Out of production
Production Range 1963-1968
Total Production 284
Data for (Version) Lockheed C-141B Starlifter
Variants C-141A, C-141B, C-141C
3-D VIEW DIAGRAM
14. Avro York
Military Transport Aircraft
The Avro York was a British transport aircraft that was derived from the
Second World War Lancaster heavy bomber, and used in both military and airliner
roles between 1943 and 1964. Avro type 685, development began in 1941. The
design paired a new "squared-off" fuselage with the wings, tail and undercarriage
of the Lancaster bomber. Production was undertaken by Avro with the hopes of
sales to the Royal Air Force and in the post war civil airliner market.
The prototype, LV626, was assembled by Avro's experimental flight
department at Manchester's Ring way Airport and first flew there on 5 July 1942.
It had initially been fitted with the twin fins and rudders of the Lancaster but the
increased fuselage side area forward of the wing compared to the Lancaster
necessitated fitting a third central fin to retain adequate control and directional
stability. Initial assembly and testing of production Yorks mainly for the RAF, was
at Ringway, later Yeadon (Leeds) and Woodford (Cheshire).
SPECIFICATIONS
Crew 5 (two pilots, navigator, wireless operator, cabin
steward)
Capacity 56 passengers
Payload 20,000 lb (9,100 kg)
Length 78 ft 6 in (23.9 m)
Wingspan 102 ft 0 in (31.1 m)
Height 16 ft 6 in (5 m)
Wing area 1,297 ft² (120.5 m²)
Empty weight 40,000 lb (18,150 kg)
Loaded weight 65,000 lb (29,480 kg)
Power plant 4× Rolls-Royce Merlin 24 liquid-cooled V12 engines,
1,280 hp (950 kW) each
Maximum speed 298 mph (258 kn, 479 km/h) at 21,000 ft (6,400 m)
Range 3,000 mi (2,600 nmi, 4,800 km)
Service ceiling 23,000 ft (7,010 m)
Rate of climb 820 ft/min (4.2 m/s)
Wing loading 54 lb/ft² (260 kg/m²)
Power/mass 0.079 hp/lb (130 W/kg)
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15. Antonov An-22
Heavy Cargo Freighter
The Antonov An-22 is a heavy four-engine turboprop long-range transport aircraft by the Soviet design bureau OKB Antonov (today Antonov ASTC, Ukraine).
Antonov designed the An-22 Antheus (named for the giant son of Greek god Poseidon) to carry the Soviet Army's mightiest fighting vehicles, including main battle tanks and missile launchers. Its NK-12 turboprops, which also power the Tu-95/Tu-142 "Bear" family of Russian bombers and maritime patrol aircraft, are the most powerful turboprop engines in service.
NATO reporting name Cock, the An-22 is a very large, long-range heavy transport. It flew for the first time in February 1965, at which time it was the largest transport aircraft in the world. Deliveries to both the Soviet Air Force and Aeroflot were completed during 1974, with the military air transport force (VTA) receiving between 30 and 50 aircraft. The An-22 is used widely in the
underdeveloped areas of the northern USSR, Siberia and the Far East. Accommodation is for a crew of five or six, 28-29 passengers in the cabin and freight. Maximum payload is 80 000kg.
In October 1967 an An-22 established 14 payload-to-height records. With a payload of 100,000kg of metal blocks it reached a height of 7,848m, thereby qualifying also for the intermediate records from 35,000kg. Max payload lifted to a height of 2,000m was 104,444.6kg. A take-off run of just over one kilometre was reported; the flight duration was 78 minutes.
SPECIFICATIONS
Crew 5-6
Propulsion 4 Turboprop Engines
Engine Model Kusnezow / Kuznetsov NK-12MA
Engine Power (each) 11030 kW 14792 shp
Speed 741 km/h 400 kts 460 mph
Service Ceiling 8.000 m 26.247 ft
Range 5.000 km 2.700 NM 3.107 mi.
Empty Weight 114.000 kg 251.327 lbs
Max. Takeoff Weight 250.000 kg 551.156 lbs
Wing Span 64,40 m 211,3 ft
Wing Area 345,0 m² 3714 ft²
Length 57,80 m 189,6 ft
Height 12,53 m 41,1 ft
First Flight 27.02.1965
Production Status Out of production
Production Range 1965-1975
Total Production 100
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