JEROEN VOGELAAR: Aviation Photographs

aircraft

Gulfstream G550

Gulfstream G550 N917GA

Gulfstream G550 is a business jet aircraft. The Gulfstream 550 has the longest flight range in its class.

 

  • Role: Business jet
  • National origin: United States of America
  • Manufacturer: Gulfstream Aerospace
  • Production line: Savannah, Georgia
  • First flight: July 18, 2002
  • Introduction: 2004
  • Status: In service
  • Produced: 2003–present
  • Number built: 300+

Specifications G550

General characteristics

  • Crew: 2 pilots, 0–2 attendants
  • Capacity: 14–19 passengers
  • Length: 96 ft 5 in (29.4 m)
  • Wingspan: 93 ft 6 in (28.5 m)
  • Height: 25 ft 10 in (7.9 m)
  • Empty weight: 48,300 lb (21,900 kg)
  • Loaded weight: 54,500 lb (24,700 kg)
  • Useful load: 6,200 lb (2,800 kg)
  • Max. takeoff weight: 91,000 lb (41,300 kg)
  • Powerplant: 2 × Rolls-Royce BR710 turbofan, 15,385 lbf (68.44 kN) each
  • Maximum Ramp Weight: 91,400 lb (41,500 kg)
  • Maximum landing weight: 75,300 lb (34,200 kg)
  • Maximum fuel weight: 41,300 lb (18,700 kg)
  • Cabin dimensions: volume: 1,669 ft³ (47.3 m³), height: 6 ft 2 in (1.88 m), width: 7 ft 4 in (2.24 m)
  • Baggage compartment volume: 226 ft³ (6.4 m³)

Performance

  • Maximum speed: 0.885 Mach (585 mph, 941 km/h)
  • Cruise speed: 488 knots (562 mph, 0.85 Mach, 904 km/h)
  • Range: 6,750 nmi (7,768 miles, 12,500 km)
  • Service ceiling: 51,000 ft (15,500 m)
  • Takeoff distance: 5,910 ft (1,800 m)
  • Landing distance: 2,770 ft (880 m)

 

Heinkel He 162

Heinkel He162A-2 Volksjäger 120076/4 Luftwaffe

The Heinkel He 162 Volksjäger, the name of a project of the Emergency Fighter Program design competition, was a German single-engine, jet-powered fighter aircraft fielded by the Luftwaffe in World War II. Designed and built quickly, and made primarily of wood.

  • Role: Fighter
  • National origin: Germany
  • Manufacturer: Heinkel
  • First flight: 6 December 1944
  • Introduction: 1945
  • Status: 9 aircraft in museums
  • Retired: 1945
  • Number built: ca 320

Specifications (He 162A)

General characteristics

  • Crew: 1, pilot with ejection seat
  • Length: 9.05 m (29 ft 8 in)
  • Wingspan: 7.2 m (23 ft 7 in)
  • Height: 2.6 m (8 ft 6 in)
  • Wing area: 11.16 m² (156 ft²)
  • Empty weight: 1,660 kg (3,660 lb)
  • Max. takeoff weight: 2,800 kg (6,180 lb)
  • Powerplant: 1 × BMW 003E-1 or E-2 (meant for dorsal fuselage attachment) axial flow turbojet, 7.85 kN (1,760 lbf)
  • Fuel capacity of 695 litres (183 US gallons), allowing maximum 30 minute mission profile

Performance

  • Maximum speed: 790 km/h (491 mph) at normal thrust at sea level; 840 km/h (522 mph) at 6000 m (19,680 ft); using short burst extra thrust 890 km/h (553 mph) at sea level and 905 km/h (562 mph) at 6000 m (19,680 ft).
  • Range: 975 km (606 mi)
  • Service ceiling: 12,000 m (39,400 ft)
  • Rate of climb: 1,405 m/min (4,615 ft/min)

Armament

  • Guns: 2 × 20 mm MG 151/20 autocannons with 120 rpg (He 162 A-2) OR 2 × 30 mm MK 108 cannons with 50 rpg (He 162 A-0, A-1)

Antonov An-12

Antonov An-12AP UR-CCP Cavok Air

The Antonov An-12 is a four-engined turboprop transport aircraft designed in the Soviet Union.

  • Role: Civil and Military transport aircraft
  • National origin: Soviet Union
  • Manufacturer: Antonov
  • First flight: 16 December 1957
  • Introduction: 1959
  • Status: Active service with various airlines (especially cargo) and Air Forces
  • Produced: 1957–1973
  • Number built: 1,248

Specifications (An-12)

General characteristics

  • Crew: 5: 2 pilots, flight engineer, navigator, radio operator
  • Payload: 20,000 kg (44,000 lb)
  • Length: 33.10 m (108 ft 7 in)
  • Wingspan: 38.00 m (124 ft 8 in)
  • Height: 10.53 m (34 ft 7 in)
  • Wing area: 121.7 m² (1,310 ft²)
  • Empty weight: 28,000 kg (62,000 lb)
  • Useful load: 60 paratroopers (two BMD-1 armoured vehicles)
  • Max. takeoff weight: 61,000 kg (130,000 lb)
  • Powerplant: 4 × Ivchenko AI-20L or AI-20M turboprops, 4,000 ehp (3,000 kW) each

Performance

  • Maximum speed: 777 km/h (419 knots, 482 mph)
  • Cruise speed: 670 km/h (361 knots, 415 mph)
  • Range:
    • With maximum fuel: 5,700 km (3,075 nm, 3,540 mi)
    • With maximum load: 3,600 km (1,945 nm, 2,235 mi))
  • Service ceiling: 10,200 m (33,500 ft)
  • Rate of climb: 10m/s (1960ft/min)

Armament

  • Guns: 2× 23 mm (0.906 in) Nudelman-Rikhter NR-23 cannons in a tail turret (some aircraft)

Yakovlev Yak-3

Yakovlev Yak-3UA F-AZXZ/4 Soviet Air Force

The Yakovlev Yak-3 was a World War II Soviet fighter aircraft.

  • Role: Fighter
  • National origin: Russia
  • Manufacturer: Yakovlev
  • First flight: 12 April 1941
  • Introduction: 1944
  • Status: Privately owned, or in museums
  • Retired: 1952
  • Number built: 4.848

Yakovlev Yak-3UA F-AZLY/5 Soviet Air Force

Military operators

  • France, Normandie-Niemen squadron
  • Air Force of the Polish Army
  • Soviet Air Force
  • SFR Yugoslav Air Force

Yakovlev Yak-3UA F-AZXZ/4 Soviet Air Force

Specifications (Yak-3)

General characteristics

  • Crew: 1
  • Length: 8.5 m (27 ft 10 in)
  • Wingspan: 9.2 m (30 ft 2 in)
  • Height: 2.39 m (7 ft 11 in)
  • Wing area: 14.85 m² (159.8 ft²)
  • Empty weight: 2,105 kg (4,640 lb)
  • Loaded weight: 2,692 kg (5,864 lb)
  • Powerplant: 1 × Klimov VK-105PF-2 V-12 liquid-cooled piston engine, 970 kW (1,300 hp)

Performance

  • Maximum speed: 655 km/h (407 mph)
  • Range: 650 km (405 miles)
  • Service ceiling: 10,700 m (35,000 ft)
  • Rate of climb: 18.5 m/s (3,645 ft/min)
  • Wing loading: 181 kg/m² (36.7 lb/ft²)
  • Power/mass: 0.36 kW/kg (0.22 hp/lb)

Armament

  • Guns:
    • 1 × 20 mm ShVAK cannon, with 150 rounds
    • 2 × 12.7 mm Berezin UBS machine guns with 170 rpg

Antonov An-2

Antonov An-2 D-FKME Donau-Air-Service

The Antonov An-2 (Russian nickname: “Annushka” or “Annie”) is a Soviet mass-produced single-engine biplane utility/agricultural aircraft.

  • Role: Agricultural and utility aircraft
  • National origin: Soviet Union
  • Manufacturer: Antonov/WSK PZL-Mielec
  • First flight: 31 August 1947
  • Introduction: 1947
  • Produced: 1947–2002
  • Number built: 18,000+

Specifications (An-2)

General characteristics

  • Crew: 1–2
  • Capacity: 12 passengers
  • Length: 12.4 m (40 ft 8 in)
  • Wingspan: ** Upper wing: 18.2 m (59 ft 8 in)
    • Lower wing: 14.2 m (46 ft 9 in))
  • Height: 4.1 m (13 ft)
  • Wing area: 71.52 m² (769.8 ft²)
  • Empty weight: 3,300 kg (7,300 lb)
  • Loaded weight: 5,440 kg (12,000 lb)
  • Useful load: 2,140 kg (4,700 lb)
  • Powerplant: 1 × Shvetsov ASh-62IR 9-cylinder supercharged radial engine, 750 kW (1,000 hp)

Performance

  • Maximum speed: 258 km/h (139 kn, 160 mph)
  • Cruise speed: 190 km/h (100 kn, 120 mph)
  • Stall speed: ~50 km/h (26 knots, 30 mph)
  • Range: 845 km (456 nmi, 525 mi)
  • Service ceiling: 4,500 m (14,750 ft)
  • Rate of climb: 3.5 m/s (700 ft/min)
  • Power/mass: 0.136 kW/kg (0.083 hp/lb)

Boeing 747

Boeing 747-406(M) PH-BFE KLM

The Boeing 747 is a wide-body commercial jet airliner and cargo aircraft.

  • Role: Wide-body, long-range jet airliner
  • National origin: United States
  • Manufacturer: Boeing Commercial Airplanes
  • First flight: February 9, 1969
  • Introduction: January 22, 1970
  • Status: In service
  • Produced: 1968–present
  • Number built: 1,502 as of January 31, 2015

Variants

Boeing 747-100

First flight: February 9, 1969

The first 747-100s were built with six upper deck windows (three per side) to accommodate upstairs lounge areas. Later, as airlines began to use the upper deck for premium passenger seating instead of lounge space, Boeing offered a ten-window upper deck as an option.

General characteristics

  • Cockpit crew: 3
  • Seating capacity: 480; optional 550 (1-class, maximum)
  • Overall length: 231 ft 10 in (70.6 m)
  • Wingspan: 195 ft 8 in (59.6 m)
  • Overall height: 63 ft 5 in (19.3 m)
  • Operating empty weight: 358,000 lb (162,400 kg)
  • Maximum take-off weight: 735,000 lb (333,390 kg)
  • Cruising speed: Mach 0.84 (555 mph, 893 km/h, 481 knots )
  • Maximum speed: Mach 0.89 (594 mph, 955 km/h, 516 kn)
  • Range fully loaded: 5,300 nmi, 6,100 mi; 9,800 km
  • Engine (× 4): PW JT9D-7A/-7F/-7J RR RB211-524B2 GE CF6-45A2 (747SR)

Boeing 747-200

First flight: October 11, 1970

747-200 – The demand for longer range aircraft with increased payload quickly led to the improved −200, which featured more powerful engines, increased MTOW, and greater range than the −100.

General characteristics

  • Cockpit crew: 3
  • Seating capacity: 480; optional 550 (1-class, maximum)
  • Overall length: 231 ft 10 in (70.6 m)
  • Wingspan: 195 ft 8 in (59.6 m)
  • Overall height: 63 ft 5 in (19.3 m)
  • Operating empty weight: 383,000 lb (174,000 kg)
  • Maximum take-off weight: 833,000 lb (377,842 kg)
  • Cruising speed: Mach 0.84 (555 mph, 893 km/h, 481 knots )
  • Maximum speed: Mach 0.89 (594 mph, 955 km/h, 516 kn)
  • Range fully loaded: 6,850 nmi 7,880 mi; 12,690 km
  • Engine (× 4): PW JT9D-7R4G2 GE CF6-50E2 RR RB211-524D4

Boeing 747-300

First flight: October 5, 1982

The 747-300 features a 23-foot-4-inch-longer (7.11 m) upper deck than the −200.

General characteristics

  • Cockpit crew: 3
  • Seating capacity: 565; optional 660 (1-class)
  • Overall length: 231 ft 10 in (70.6 m)
  • Wingspan: 195 ft 8 in (59.6 m)
  • Overall height: 63 ft 5 in (19.3 m)
  • Operating empty weight: 392,800 lb (178,100 kg)
  • Maximum take-off weight: 833,000 lb (377,842 kg)
  • Cruising speed: Mach 0.84 (555 mph, 893 km/h, 481 knots )
  • Maximum speed: Mach 0.89 (594 mph, 955 km/h, 516 kn)
  • Range fully loaded: 6,700 nmi 7,700 mi; 12,400 km
  • Engine (× 4): PW JT9D-7R4G2 GE CF6-80C2B1 RR RB211-524D4

Boeing 747-400ER

First flight: April 29, 1988

The 747-400 introduced a new glass cockpit designed for a flight crew of two instead of three, with a reduction in the number of dials, gauges and knobs from 971 to 365 through the use of electronics. The type also features tail fuel tanks, revised engines, and a new interior.

General characteristics

  • Cockpit crew: 2
  • Seating capacity: 565; optional 660 (1-class)
  • Overall length: 231 ft 10 in (70.6 m)
  • Wingspan: 211 ft 5 in (64.4 m)
  • Overall height: 63 ft 6 in (19.4 m)
  • Operating empty weight: 406,900 lb (184,600 kg)
  • Maximum take-off weight: 910,000 lb (412,775 kg)
  • Cruising speed: Mach 0.855 (570 mph, 918 km/h, 495 kn)
  • Maximum speed: Mach 0.92 (614 mph, 988 km/h, 533 kn)
  • Range fully loaded: 7,670 nmi 8,830 mi; 14,200 km
  • Engine (× 4): PW 4062 GE CF6-80C2B5F RR RB211-524G/H ER: GE CF6-80C2B5F

Boeing 747-8I

First flight: March 20, 2011

The 747-800 uses the same engine and cockpit technology as the 787, hence the use of the “8”. The variant is designed to be quieter, more economical, and more environmentally friendly. The 747-8’s fuselage is lengthened from 232 to 251 feet (70.8 to 76.4 m), marking the first stretch variant of the aircraft. Power is supplied by General Electric GEnx-2B67 engines.

General characteristics

  • Cockpit crew: 2
  • Seating capacity: 605 (maximum)
  • Overall length: 250 ft 2 in (76.25 m)
  • Wingspan: 224 ft 7 in (68.5 m)
  • Overall height: 63 ft 6 in (19.4 m)
  • Operating empty weight: 472,900 lb (214,503 kg)
  • Maximum take-off weight: 987,000 lb (447,696 kg)
  • Cruising speed: Mach 0.855 (570 mph, 918 km/h, 495 kn)
  • Maximum speed: Mach 0.92 (614 mph, 988 km/h, 533 kn)
  • Range fully loaded: 8,000 nmi 9,200 mi; 15,000 km
  • Engine (× 4): GEnx-2B67

Dassault Falcon 900

Dassault Falcon 900LX HB-JTA Air Sarina AG

The Dassault Falcon 900 is a French-built corporate jet aircraft made by Dassault Aviation

  • Role: Business jet
  • National origin: France
  • Manufacturer: Dassault Aviation
  • First flight: 21 September 1984
  • Status: In service
  • Produced: 1984-present
  • Number built: 260+
  • Developed from: Dassault Falcon 50
  • Variants: Dassault Falcon 2000, Dassault Falcon 7X

Specifications (Falcon 900B)

General characteristics

  • Crew: Two
  • Capacity: 19 passengers
  • Length: 20.21 m (66 ft 4 in)
  • Wingspan: 19.33 m (63 ft 5 in)
  • Height: 7.55 m (24 ft 9.5 in)
  • Wing area: 49 m² (527 ft²)
  • Empty weight: 10,255 kg (22,608 lb)
  • Max. takeoff weight: 20,640kg (45,503 lb)
  • Powerplant: 3 × Honeywell TFE731-5BR-1C turbofan, 21.13 kN (4,750 lbf) each

Performance

  • Maximum speed: Mach 0.84-0.87
  • Cruise speed: 950 km/h (513 knots, 590 mph) at 36,000ft (10,970 m) (Mach 0.85)
  • Stall speed: 158 km/h (85 knots, 98 mph) (wheels and flaps down)
  • Range: 7,400 km (3,995 nm, 4,598 mi) (7 passengers)
  • Service ceiling: 15,500 m (51,000 ft)
  • Wing loading: 435kg/m² (91lb/ft²)

 

Pilatus PC-6 Porter

Pilatus PC-6B2-H4 Turbo Porter HB-FNI Pilatus Aircraft

The Pilatus PC-6 Porter is a single-engined Short Take-Off and Landing (STOL) utility aircraft designed by Pilatus Aircraft of Switzerland. It has been built in both piston engine and turboprop powered versions (Turbo-Porter) and was produced for a time by Fairchild Hiller in the United States.

  • Role: STOL Passenger and utility aircraft
  • National origin: Switzerland
  • Manufacturer: Pilatus Aircraft
  • First flight: Porter – 4 May 1959, Turbo-Porter – 2 May 1961.
  • Produced: 1959-present
  • Number built:581 (As of August 2014)
  • Status: Active service

Military variants

Specifications PC-6 B2 Turbo-Porter

General characteristics

  • Crew: one, pilot
  • Capacity: up to ten passengers
  • Payload: 1,130 kg (2,491 lb)
  • Length: 11.00 m (36 ft 1 in)
  • Wingspan: 15.87 m (52 ft 0¾ in)
  • Height: 3.20 m (10 ft 6 in)
  • Wing area: 30.15 m² (324.5 sq ft)
  • Airfoil: NACA 64-514
  • Aspect ratio: 8.4:1
  • Empty weight: 1,270 kg (2,800 lb)
  • Max. takeoff weight: 2,800 kg (6,173 lb)
  • Powerplant: 1 × Pratt & Whitney Canada PT6A-27 turboprop, 410 kW (550 shp)(downrated from 507 kW (680 shp))

Performance

  • Never exceed speed: 280 km/h (151 knots, 174 mph)
  • Maximum speed: 232 km/h (125 knots, 144 mph)
  • Cruise speed: 213 km/h (115 knots, 132 mph) at 3,050 m (10,000 ft)
  • Stall speed: 96 km/h (52 knots, 60 mph) (flaps down, power off)
  • Range: 730 km (394 nmi, 453 mi) with maximum payload
  • Ferry range: 1,612 km (870 nmi, 1,002 mi) with maximum internal and underwing fuel
  • Service ceiling: 8,197 m (25,000 ft)
  • Rate of climb: 4.8 m/s (941 ft/min)

Dassault Rafale

Dassault Rafale M 38 French Navy

The Dassault Rafale is a French twin-engine, canard delta-wing, multirole fighter aircraft designed and built by Dassault Aviation. Equipped with a wide range of weapons, the Rafale is intended to perform air supremacy, interdiction, aerial reconnaissance, and nuclear strike missions.

  • Role: Multirole fighter aircraft
  • National origin: France
  • Manufacturer: Dassault Aviation
  • First flight: 4 July 1986
  • Introduction: 18 May 2001
  • Status: In service
  • Produced: 1986–present
  • Number built: 133 (as of October 2014)

Military operators

  • French Air Force 180 have been ordered
  • French Navy
  • Egyptian Air Force 24 on order

Variants

  • Rafale A – Technology demonstrator, first flying in 1986
  • Rafale B – Two-seater version for the French Air Force
  • Rafale C – Single-seat version for the French Air Force
  • Rafale M – Carrier-borne version for the French Naval Aviation

Specifications

General characteristics

  • Crew: 1–2
  • Length: 15.27 m (50.1 ft)
  • Wingspan: 10.80 m (35.4 ft)
  • Height: 5.34 m (17.5 ft)
  • Wing area: 45.7 m² (492 ft²)
  • Empty weight:
    • C: 9,500 kilograms (20,900 lb)
    • B: 9,770 kilograms (21,540 lb)
    • M: 10,196 kilograms (22,480 lb)
  • Loaded weight: 14,016 kg (30,900 lb)
  • Max. takeoff weight: 24,500 kg (C/D), 22,200 kg (M) (54,000 lb)
  • Powerplant: 2 × Snecma M88-2 turbofans
    • Dry thrust: 50.04 kN (11,250 lbf) each
    • Thrust with afterburner: 75.62 kN (17,000 lbf) each
  • Fuel capacity: 4,700 kg (10,360 lb) internal

Performance

  • Maximum speed:
    • High altitude: Mach 1.8 (1,912 km/h, 1,032 knots)
    • Low altitude: Mach 1.1 (1,390 km/h, 750 knots)
  • Range: 3,700+ km (2,000+ nmi)  with 3 drop tanks
  • Combat radius: 1,852+ km (1,000+ nmi) on penetration mission
  • Service ceiling: 15,235 m (50,000 ft)
  • Rate of climb: 304.8+ m/s (60,000+ ft/min)
  • Wing loading: 306 kg/m² (62.8 lb/ft²)
  • Thrust/weight: 0.988 (100% fuel, 2 EM A2A missile, 2 IR A2A missile) version M
  • Maximum g-load: +9/–3.6 g

Armament

  • Guns: 1× 30 mm (1.18 in) GIAT 30/M791 autocannon with 125 rounds
  • Hardpoints: 14 for Air Force versions (Rafale B/C), 13 for Navy version (Rafale M) with a capacity of 9,500 kg (20,900 lb) external fuel and ordnance and provisions to carry combinations of:
    • Missiles:
      • MBDA MICA IR or EM or Magic II and
      • MBDA Meteor air-to-air missiles in the future
    • Air-to-ground:
      • MBDA Apache or
      • Storm Shadow-SCALP EG or
      • AASM-Hammer or
      • GBU-12 Paveway II or GBU-49 Enhanced Paveway II
      • GBU-24 Paveway III
      • AS-30L
    • Air-to-surface:
      • AM 39-Exocet
      • CVS401-Perseus
    • Deterrence:
      • ASMP-A nuclear missile
    • Other:
      • Thales Damocles targeting pod
      • AREOS (Airborne Recce Observation System)reconnaissance pod
      • up to 5 drop tanks
      • Buddy-buddy refuelling pod

Avionics

  • Thales RBE2 radar
  • Thales SPECTRA electronic warfare system.
  • Thales/SAGEM-OSF Optronique Secteur Frontal infra-red search and track system.

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