Lockheed P-38 Lightning

The Lockheed P-38 Lightning was a World War II American fighter aircraft built by Lockheed. Developed to a United States Army Air Corps requirement, the P-38 had distinctive twin booms and a single, central nacelle containing the cockpit and armament. Named "fork-tailed devil" by the Luftwaffe and "two planes, one pilot" by the Japanese, the P-38 was used in a number of roles, including dive bombing, level bombing,ground-attack, night fighting, photo reconnaissance missions,and extensively as a long-range escort fighter when equipped with drop tanks under its wings.

The P-38 was used most successfully in the Pacific Theater of Operations and the China-Burma-India Theater of Operations as the mount of America's top aces, Richard Bong (40 victories) and Thomas McGuire (38 victories). In the South West Pacific theater, the P-38 was the primary long-range fighter of United States Army Air Forces until the appearance of large numbers ofP-51D Mustangs toward the end of the war.

The P-38 was unusually quiet for a fighter, the exhaust muffled by the turbo-superchargers. It was extremely forgiving, and could be mishandled in many ways, but the rate of roll in the early versions was too slow for it to excel as a dogfighter. The P-38 was the only American fighter aircraft in production throughout American involvement in the war, from Pearl Harbor to Victory over Japan Day.

General characteristics

• Crew: One
• Length: 37 ft 10 in (11.53 m) (11.53 m)
• Wingspan: 52 ft 0 in (15.85 m) (15.85 m)
• Height: 12 ft 10 in (3.91 m) (3.91 m)
• Wing area: 327.5 ft² (30.43 m²)
• Airfoil: NACA 23016 / NACA 4412
• Empty weight: 12,800 lb (5,800 kg)
• Loaded weight: 17,500 lb (7,940 kg)
• Max. takeoff weight: 21,600 lb (9,798 kg)
• Powerplant: 2 × Allison V-1710-111/113 V-12 piston engine, 1,600 hp (1,193 kW) WEP at 60 inHg, 3,000 rpm  each
• Zero-lift drag coefficient: 0.0268
• Drag area: 8.78 ft² (0.82 m²)
• Aspect ratio: 8.26

Performance

• Maximum speed: 414 mph (667 km/h) on Military Power: 1,425 hp at 54 inHg, 3,000 rpm at 25,000 ft (7,620 m)
• Stall speed: 105 mph (169 km/h) (170 km/h)
• Range: 1,300 mi (2,100 km) combat (1,770 km / 3,640 km)
• Service ceiling: 44,000 ft (13,000 m) (13,400 m)
• Rate of climb: 4,750 ft/min (24.1 m/s) maximum
• Wing loading: 53.4 lb/ft² (260.9 kg/m²)
• Power/mass: 0.16 hp/lb (0.27 kW/kg)
• Lift-to-drag ratio: 13.5

Armament

• 1× Hispano M2(C) 20 mm cannon with 150 rounds
• 4× M2 Browning machine gun 0.50 in (12.7 mm) machine guns with 500 rpg.

• 4× M10 three-tube 4.5 in (112 mm) rocket launchers; or:
  • Inner hardpoints:
    • 2× 2,000 lb (907 kg) bombs or drop tanks; or
    • 2× 1,000 lb (454 kg) bombs or drop tanks, plus either
      • 4× 500 lb (227 kg) bombs or
      • 4× 250 lb (113 kg) bombs; or
    • 6× 500 lb (227 kg) bombs; or
    • 6× 250 lb (113 kg) bombs
  • Outer hardpoints:
    • 10× 5 in (127 mm) HVARs (High Velocity Aircraft Rockets); or
    • 2× 500 lb (227 kg) bombs; or
    • 2× 250 lb (113 kg) bombs

Lockheed JetStar

The Lockheed JetStar (company designations L-329 and L-1329; designated C-140 in USAF service) is a business jetproduced from the early 1960s to the 1970s. The JetStar was the first dedicated business jet to enter service. It was also one of the largest aircraft in the class for many years, seating ten plus two crew. It is distinguishable from other small jets by its four engines, mounted on the rear of the fuselage in a similar layout to the larger Vickers VC10 airliner that first flew several years later, and the "slipper"-style fuel tanks fixed to the wings.

General characteristics

• Crew: two pilots & typically one flight attendant
• Capacity: 8-10 passengers
• Length: 60 ft 5 in (18.41 m)
• Wingspan: 54 ft 5 in (16.59 m)
• Height: 20 ft 5 in (6.22 m)
• Wing area: 542.5 ft² (50.4 m²)
• Empty weight: 24,750 lb (11,226 kg)
• Loaded weight: 41,535 lb (18,840 kg)
• Max. takeoff weight: 44,500 lb (20,185 kg)
• Powerplant: 4 × Garrett TFE731-3 turbofan, 3,700 lbf (16.5 kN) each

Performance

• Maximum speed: 547 mph (476 knots, 883 km/h) at 30,000 ft (9,145 m)
• Cruise speed: 504 mph (438 knots, 811 km/h)
• Range: 2,995 mi (2,604 nmi, 4,820 km)
• Service ceiling: 43,000 ft (13,105 m)
• Rate of climb: 4,150 ft/min (21.1 m/s)

Lockheed C-130 Hercules

The Lockheed C-130 Hercules is a four-engine turboprop military transport aircraft designed and built originally by Lockheed, now Lockheed Martin. 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 a gunship (AC-130), for airborne assault, search and rescue, scientific research support, weather reconnaissance,aerial refueling, maritime patrol, and aerial firefighting. It is now the main tactical airlifter for many military forces worldwide. Over 40 models and variants of the Hercules serve with more than 60 nations.

The C-130 entered service with U.S. in the 1950s, followed by Australia and others. During its years of service, the Hercules family has participated in numerous military, civilian and humanitarian aid operations. The family has the longest continuous production run of any military aircraft in history. In 2007, the C-130 became the fifth aircraft—after the English Electric Canberra,Boeing B-52 Stratofortress, Tupolev Tu-95, and Boeing KC-135 Stratotanker, all designs with various forms of aviation gas turbine powerplants—to mark 50 years of continuous use with its original primary customer, in this case, the United States Air Force. The C-130 is one of the only military aircraft to remain in continuous production for over 50 years with its original customer, as the updated C-130J Super Hercules.

General characteristics

• Crew: five (two pilots, navigator, flight engineer and loadmaster)
• Capacity:
  • C-130E/H/J cargo hold: length, 40 feet (12.31 meters); width, 119 inches (3.12 meters); height, 9 feet (2.74 meters). Rear ramp: length, 123 inches (3.12 meters); width, 119 inches (3.02 meters)
  • C-130J-30 cargo hold: length, 55 feet (16.9 meters); width, 119 inches (3.12 meters); height, 9 feet (2.74 meters). Rear ramp: length, 123 inches (3.12 meters); width, 119 inches (3.02 meters)
  • 92 passengers or
  • 64 airborne troops or
  • 74 litter patients with 5 medical crew or
  • 6 pallets or
  • 2–3 Humvees or
  • 2 M113 armored personnel carriers
• Payload: 45,000 lb (20,400 kg)
• Length: 97 ft 9 in (29.8 m)
• Wingspan: 132 ft 7 in (40.4 m)
• Height: 38 ft 3 in (11.6 m)
• Wing area: 1,745 ft² (162.1 m²)
• Empty weight: 75,800 lb (34,400 kg)
• Useful load: 72,000 lb (33,000 kg)
• Max. takeoff weight: 155,000 lb (70,300 kg)
• Powerplant: 4 × Allison T56-A-15 turboprops, 4,590 shp (3,430 kW) each
• Propellers: 4 propellers
  • Propeller diameter: 13.5 ft (4.1 m)

Performance

• Maximum speed: 320 knots (366 mph, 592 km/h) at 20,000 ft (6,060 m)
• Cruise speed: 292 kts (336 mph, 540 km/h)
• Range: 2,050 nmi (2,360 mi, 3,800 km)
• Service ceiling: 33,000 ft (10,060 m) empty; 23,000 ft (7,077 m) with 42,000 pounds (19,090 kilograms) payload ()
• Rate of climb: 1,830 ft/min (9.3 m/s)
• Takeoff distance: 3,586 ft (1,093 m) at 155,000 lb (70,300 kg) max gross weight;^[ 1,400 ft (427 m) at 80,000 lb (36,300 kg) gross weight

Avionics

• Westinghouse Electronic Systems (now Northrop Grumman) AN/APN-241 weather and navigational radar

Sikorsky SH-3 Sea King

The Sikorsky SH-3 Sea King (company designation S-61) is an American twin-engined anti-submarine warfare (ASW)helicopter designed and built by Sikorsky Aircraft. It was a landmark design, being one of the first ASW helicopter to take advantage of turboshaft engines, as well as being the first amphibious helicopter in the world.^[2]

Introduced in 1961, it served as the United States Navy as a key ASW and utility asset for several decades before being replaced by the non-amphibious Sikorsky SH-60 Seahawk in the 1990s. The type also proved popular in civil service and with foreign military customers, as of 2014 many remain in service in a number of nations around the world. The Sea King has been built under license by Agusta in Italy, Mitsubishi in Japan, and by Westland in the United Kingdom (See Westland Sea King). The major civil versions are the S-61L and S-61N.

OPERATIONAL HISTORY

The Sea King became operational with the United States Navy in June 1961 as the HSS-2; the aircraft's designation subsequently changed to SH-3A when the unified aircraft designation system was introduced. It was used primarily for anti-submarine warfare, detecting and tracking Soviet submarines and, in time of war, would be used to attack enemy submarines as well. Nighttime ASW operations were possible with considerable difficulty; in the event of hostilities, Sea Kings could also operate effectively from offshore platforms in order to further their surveillance and strike range

General characteristics

• Crew: four (two pilots, two ASW systems operators)
• Capacity: three passengers
• Length: 54 ft 9 in (16.7 m)
• Rotor diameter: 62 ft (19 m)
• Height: 16 ft 10 in (5.13 m)
• Disc area: ft² (m²)
• Empty weight: 11,865 lb (5,382 kg)
• Loaded weight: 18,626 lb (8,449 kg)
• Max. takeoff weight: 22,050 lb (10,000 kg)
• Powerplant: 2 × General Electric T58-GE-10 turboshafts, 1,400 shp (1045 kW) each

Performance

• Maximum speed: 166 mph (267 km/h)
• Range: 621 mi (1,000 km)
• Service ceiling: 14,700 ft (4,481 m)
• Rate of climb: 1,310-2,220 ft/min (400-670 m/min)

Armament

• 2× Mk 46/44 anti-submarine torpedoes (SH-3H)
• Various sonobuoys and pyrotechnic devices
• B-57 Nuclear depth charge

Douglas A-20 Havoc

The Douglas A-20 Havoc (company designation DB-7) was an American attack, light bomber, intruder and night fighter aircraft of World War II. It served with several Allied air forces, principally the United States Army Air Forces (USAAF), the Soviet Air Forces (VVS), Soviet Naval Aviation (AVMF) and the Royal Air Force (RAF) of the United Kingdom. Soviet units received more than one in three (2,908 aircraft) of the DB-7s ultimately built. It was also used by the air forces of Australia, South Africa,France, and the Netherlands during the war, and by Brazil afterwards.

In British Commonwealth air forces, bomber/attack variants of the DB-7 were usually known by the service name Boston, while night fighter and intruder variants were usually known as Havoc. An exception to this was the Royal Australian Air Force, which referred to all variants of the DB-7 by the name Boston. The USAAF referred to night fighter variants as P-70.

General characteristics

• Crew: 2-3
• Length: 47 ft 11 in (14.63 m)
• Wingspan: 61 ft 4 in (18.69 m)
• Height: 17 ft 7 in (5.36 m)
• Wing area: 465 ft² (43.2 m²)
• Empty weight: 15,051 lb (6,827 kg)
• Loaded weight: 27,200 lb (12,338 kg)
• Max. takeoff weight: 27,200lb (12338 kg) (9,215 kg)
• Powerplant: 2 × Wright R-2600-A5B "Twin Cyclone" radial engines, 1,700 hp (1,268 kW) each

Performance

• Maximum speed: 339 mph (295 kn, 546 km/h) at 10,000 ft (3,050 m)
• Range: 1,050 mi (912 nmi, 1,690 km)
• Service ceiling: 23,700 ft (7,225 m)
• Rate of climb: 2,000 ft/min (10.2 m/s)

Armament

• Guns: ** 4× fixed 0.303 in (7.7 mm) Browning machine guns in the nose
  • 2× flexible 0.303 in (7.7 mm) Browning machine guns, mounted dorsally
  • 1× flexible 0.303 in (7.7 mm) Vickers K machine gun, mounted ventrally
• Bombs: 2,000 lb (910 kg)

Douglas A-1 Skyraider

The Douglas A-1 Skyraider (formerly AD) was an American single-seat attack aircraft that saw service between the late 1940s and early 1980s. It became a piston-powered, propeller-driven anachronism in the jet age, and was nicknamed "Spad", after the French World War I fighter. The Skyraider had a remarkably long and successful career, even inspiring its straight-winged, slow-flying, jet-powered successor, the A-10 Thunderbolt II. It was operated by the United States Navy (USN), the United States Marine Corps (USMC) and the United States Air Force(USAF), and also saw service with the British Royal Navy, the French Air Force, the Air Force of the Republic of Vietnam(VNAF), and others.

General characteristics

• Crew: One
• Length: 38 ft 10 in (11.84 m)
• Wingspan: 50 ft 0¼ in (15.25 m)
• Height: 15 ft 8¼ in (4.78 m)
• Wing area: 400.3 ft² (37.19 m²)
• Empty weight: 11,968 lb (5,429 kg)
• Loaded weight: 18,106 lb (8,213 kg)
• Max. takeoff weight: 25,000 lb (11,340 kg)
• Powerplant: 1 × Wright R-3350-26WA radial engine, 2,700 hp (2,000 kW)

Performance

• Maximum speed: 322 mph (280 kn, 518 km/h) at 18,000 ft (5,500 m)
• Cruise speed: 198 mph (172 kn, 319 km/h)
• Range: 1,316 mi (1,144 nmi, 2,115 km)
• Service ceiling: 28,500 ft (8,685 m)
• Rate of climb: 2,850 ft/min (14.5 m/s)
• Wing loading: 45 lb/ft² (220 kg/m²)
• Power/mass: 0.15 hp/lb (250 W/kg)

Convair F2Y Sea Dart

The Convair F2Y Sea Dart was a unique American seaplane fighter aircraft that rode on twin hydro-skis for takeoff. It flew only as a prototype, and never entered production. It is the only seaplane to have exceeded the speed of sound.

General characteristics

• Crew: one
• Length: 52 ft 7 in (16 m)
• Wingspan: 33 ft 8 in (10.3 m)
• Height: 16 ft 2 in (4.9 m)
• Wing area: 568 ft² (53 m²)
• Empty weight: 12,625 lb (5,730 kg)
• Loaded weight: 16,500 lb (7,480 kg)
• Max. takeoff weight: 21,500 lb (9,750 kg)
• Powerplant: 2 × Westinghouse J46-WE-2 {testbed: J43-WE-32 w/ 3,400 lbf each.^[8]} turbojets, 6,100.^[9] lbf (27 kN) each

Performance (estimated^[10])

• Maximum speed: 825 mph (1,325 km/h)
• Range: 513 mi (446 nm, 826 km)
• Service ceiling: 54,800 ft (16,700 m)
• Rate of climb: 17,100 ft/min (86.7 m/s)
• Wing loading: 29.0 lb/ft² (142 kg/m²)
• Thrust/weight: .56 (max loaded).96 (empty)

CESSNA 150

The Cessna 150 is a two-seat tricycle gear general aviation airplane that was designed for flight training, touring and personal use.^[1]

The Cessna 150 is the fifth most produced civilian plane ever, with 23,839 aircraft produced.^[2] The Cessna 150 was offered for sale in the 150 basic model, Commuter, Commuter II, Patroller and the aerobatic Aerobat models.

FLIGHT CHARACTERISTICS

The Cessna 150 is simple, robust, and easy to fly. For these reasons it has become one of the world's most popular basic trainers.

Cockpit visibility is generally good other than directly above the aircraft, where the view is blocked by the wing. This obstruction is of particular concern when, as is the case with most high-wing aircraft, the inside-turn wing blocks vision in the direction of a turn. As a partial remedy to this some 150s, including all Aerobats, feature a pair of overhead skylights.

Due to its light weight and light wing loading (10 lb/sq ft), the aircraft is sensitive to turbulence.

Power-on and power-off stalls are easily controlled. Normal spin recovery techniques are highly effective.

The aircraft is popular with flying schools as well as private individuals.

General characteristics

• Crew: one
• Capacity: one passenger (plus two children, limited to 60kgs with optional rear child seat)
• Length: 24 ft 9 in (7.3 m)
• Wingspan: 33 ft 4 in (10.2 m)
• Height: 8 ft 6 in (2.6 m)
• Wing area: 160 ft² (15 m²)
• Empty weight: 1,111 lb (504 kg)
• Useful load: 490 lb (220 kg)
• Max. takeoff weight: 1,600 lb (730 kg)
• Powerplant: 1 × Continental O-200-A flat-4 engine, 100 hp (75 kW) at 2,750 rpm
• Propeller diameter: 5 ft 9 in (1.8 m)

Performance

• Never exceed speed: 141 knots (162 mph, 259 km/h)
• Cruise speed: 107 knots (123 mph, 198 km/h)
• Stall speed: 42 knots (48 mph, 78 km/h)
• Range: 366 nm (421 mi, 678 km)
• Service ceiling: 14,000 ft (4,300 m)
• Rate of climb: 670 ft/min (3.4 m/s)
• lift-to-drag: 7
• Fuel consumption: 6 US gal/h (23 L/h) of avgas
• Max. wing loading: 10 lb/ft² (49 kg/m²)
• Minimum power/mass: 0.063 hp/lb (100 W/kg)

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