JEROEN VOGELAAR: Aviation Photographs

long-range

North American P-51 Mustang

North American P-51D Mustang H-307 Royal Netherlands Air Force

The North American Aviation P-51 Mustang was an American long-range, single-seat fighter and fighter-bomber used during World War II, the Korean War and other conflicts. The Mustang was conceived, designed and built by North American Aviation (NAA) in response to a specification issued directly to NAA by the British Purchasing Commission.

  • Role: Fighter
  • National origin: United States
  • Manufacturer: North American Aviation
  • First flight: October 26, 1940
  • Introduction: 1942
  • Status: Retired from military service 1984 (Dominican Air Force)
  • Number built: 15,000+

Specifications (P-51D Mustang)

General characteristics

  • Crew: 1
  • Length: 32 ft 3 in (9.83 m)
  • Wingspan: 37 ft 0 in (11.28 m)
  • Height: 13 ft 4½ in (4.08 m:tail wheel on ground, vertical propeller blade.)
  • Wing area: 235 sq ft (21.83 m²)
  • Airfoil: NAA/NACA 45-100 / NAA/NACA 45-100
  • Empty weight: 7,635 lb (3,465 kg)
  • Loaded weight: 9,200 lb (4,175 kg)
  • Max. takeoff weight: 12,100 lb (5,490 kg)
  • Powerplant: 1 × Packard V-1650-7 liquid-cooled supercharged V-12, 1,490 hp (1,111 kW) at 3,000 rpm; 1,720 hp (1,282 kW) at WEP
  • Zero-lift drag coefficient: 0.0163
  • Drag area: 3.80 sqft (0.35 m²)
  • Aspect ratio: 5.83

Performance

  • Maximum speed: 437 mph (380 kn, 703 km/h) at 25,000 ft (7,600 m)
  • Cruise speed: 362 mph (315 kn, 580 km/h)
  • Stall speed: 100 mph (87 kn, 160 km/h)
  • Range: 1,650 mi (1,434 nmi, 2,755 km) with external tanks
  • Service ceiling: 41,900 ft (12,800 m)
  • Rate of climb: 3,200 ft/min (16.3 m/s)
  • Wing loading: 39 lb/sqft (192 kg/m²)
  • Power/mass: 0.18 hp/lb (300 W/kg)
  • Lift-to-drag ratio: 14.6
  • Recommended Mach limit 0.8

Armament

  • 6× 0.50 caliber (12.7mm) M2 Browning machine guns with 1,880 total rounds (400 rounds for each on the inner pair, and 270 rounds for each of the outer two pair)
  • 2× hardpoints for up to 2,000 lb (907 kg) of bombs
  • 6 or 10× T64 5.0 in (127 mm) H.V.A.R rockets (P-51D-25, P-51K-10 on)

Boeing 767

Boeing 767-300ER N647UA United Airlines

The Boeing 767 is a mid- to large-size, long-range, wide-body twin-engine jet airliner built by Boeing Commercial Airplanes. It was the manufacturer’s first wide-body twinjet and its first airliner with a two-crew glass cockpit.

  • Role: Wide-body jet airliner
  • National origin: United States
  • Manufacturer: Boeing Commercial Airplanes
  • First flight: 767-200ER September 26, 1981, 767-300ER December 9, 1986, 767-400ER October 9, 1999
  • Introduction: September 8, 1982 with United Airlines
  • Status: In service
  • Produced: 1981–present
  • Number built: 1,069 through January 2015

Military variants

  • 767 Airborne Surveillance Testbed – – the Airborne Optical Adjunct (AOA) was modified from the prototype 767-200 for a United States Army program
  • E-767 – the Airborne Early Warning and Control (AWACS) platform for the Japan Self-Defense Forces
  • KC-767 Advanced Tanker – the 767-200ER-based aerial tanker developed for the USAF KC-X tanker competition
  • KC-767 Tanker Transport – the 767-200ER-based aerial refueling platform operated by the Italian Air Force (Aeronautica Militare), and the Japan Self-Defense Forces
  • Tanker conversions – the 767 MMTT or Multi-Mission Tanker Transport is a 767-200ER-based aircraft operated by the Colombian Air Force

Specifications

General characteristics

Boeing 767-200ER

  • Cockpit crew: 2
  • Seating capacity: 255, optional 290 (1-class)
  • Overall length: 159 ft 2 in (48.5 m)
  • Wingspan: 156 ft 1 in (47.6 m)
  • Overall height: 15,85 m.
  • Fuselage width: 16 ft 6 in (5.03 m)
  • Fuselage Height: 17 ft 9 in (5.41 m)
  • Operating empty weight: 181,610 lb (82,380 kg)
  • Maximum take-off weight: 395,000 lb (179,170 kg)
  • Service ceiling: 11.887 m
  • Cruising speed: Mach 0.80 (470 knots, 530 mph, 851 km/h at 35,000 ft (11,000 m) cruise altitude)
  • Maximum speed: Mach 0.86 (493 knots, 567 mph, 913 km/h at 35,000 ft (11,000 m) cruise altitude)
  • Range fully loaded: 6,385 nmi (7,348 mi; 11,825 km)
  • Engine (× 2): P&W PW4052, or 4056, GE CF6-80C2, RR RB211-524G or H
  • Thrust: PW: 63,300 lb (282 kN), GE: 62,100 lbf (276 kN)

Boeing 767-300ER

  • Cockpit crew: 2
  • Seating capacity: 290; optional 350 (1-class)
  • Overall length: 180 ft 3 in (54.9 m)
  • Wingspan: 156 ft 1 in (47.6 m)
  • Overall height: 15,85 m.
  • Fuselage width: 16 ft 6 in (5.03 m)
  • Fuselage Height: 17 ft 9 in (5.41 m)
  • Operating empty weight: 198,440 lb (90,010 kg)
  • Maximum take-off weight: 412,000 lb (186,880 kg)
  • Service ceiling: 11.887 m
  • Cruising speed: Mach 0.80 (470 knots, 530 mph, 851 km/h at 35,000 ft (11,000 m) cruise altitude)
  • Maximum speed: Mach 0.86 (493 knots, 567 mph, 913 km/h at 35,000 ft (11,000 m) cruise altitude)
  • Range fully loaded: 6,310 nmi (7,260 mi; 11,690 km)
  • Engine (× 2): P&W PW4056, 4060, or 4062. GE CF6-80C2. RR RB211-524G, or H
  • Thrust: PW: 63,300 lbf (282 kN), GE: 62,100 lbf (276 kN), RR: 59,500 lbf (265 kN)

Boeing 767-400ER

  • Cockpit crew: 2
  • Seating capacity: 375 (1-class)
  • Overall length: 201 ft 4 in (61.4 m)
  • Wingspan: 170 ft 4 in (51.9 m)
  • Overall height: 15,85 m.
  • Fuselage width: 16 ft 6 in (5.03 m)
  • Fuselage Height: 17 ft 9 in (5.41 m)
  • Operating empty weight: 229,000 lb (103,870 kg)
  • Maximum take-off weight: 395,000 lb (179,170 kg)
  • Service ceiling: 11.887 m
  • Cruising speed: Mach 0.80 (470 knots, 530 mph, 851 km/h at 35,000 ft (11,000 m) cruise altitude)
  • Maximum speed: Mach 0.86 (493 knots, 567 mph, 913 km/h at 35,000 ft (11,000 m) cruise altitude)
  • Range fully loaded: 5,625 nmi (6,473 mi; 10,418 km)
  • Engine (× 2): P&W PW4062 GE CF6-80C2
  • Thrust: PW: 63,300 lbf (282 kN) GE: 63,500 lbf (282 kN)

Solar Impulse

Solar Impulse 2 HB-SIB

Solar Impulse is a Swiss long-range solar-powered aircraft project. It is led by Swiss psychiatrist and aeronaut Bertrand Piccard, who co-piloted the first balloon to circle the world non-stop, and Swiss businessman André Borschberg. The privately financed project hopes to achieve the first circumnavigation of the Earth by a piloted fixed-wing aircraft using only solar power.

  • Role: Experimental solar-powered aircraft
  • National origin: Switzerland
  • Manufacturer: Solar Impulse
  • First flight: Solar Impulse HB-SIA 3 December 2009, Solar Impulse 2 HB-SIB 2 June 2014
  • Number built: 2

Specifications Solar Impulse 2 HB-SIB

General characteristics

  • Crew: 1
  • Length: 22.4 m (73.5 ft)
  • Wingspan: 71.9 m (236 ft)
  • Height: 6.37 m (20.9 ft)
  • Wing area: 17,248 photovoltaic cells (269.5 m2)
  • Loaded weight: 2,300 kg (5,100 lb)
  • Powerplant: 4 × electric motors, 4 lithium-ion batteries (633 kg), providing 13 kW (17.4 HP) each
  • Propeller diameter: 4 m (13.1 ft)
  • Take-off speed: 35 kilometres per hour (22 mph)

Performance

  • Maximum speed: 77 kts (140 km/h) 49 kts
  • Cruise speed: 90 km/h
  • Service ceiling: 8,500 m (27,900 ft) with a maximum altitude of 12,000 metres (39,000 ft)

Planned circumnavigation flight

The flight is expected to circle the world in the northern hemisphere; the closest it will get to the equator will be a flyby of Honolulu at 21.3° N. Five stops are planned to allow changes of pilots. Each leg of the flight will last three to four days, limited by the physiology of each pilot.

The route is expected to be as follows:

  • Abu Dhabi to Muscat, Oman
  • Across the Arabian Sea to Ahmedabad and Varanasi, India
  • Mandalay, Myanmar
  • Chongqing and Nanjing, China
  • Across the Pacific Ocean to Hawaii and then Phoenix, Arizona
  • New York
  • Across the Atlantic Ocean to either southern Europe or Morocco
  • Finally to Abu Dhabi