JEROEN VOGELAAR: Aviation Photographs

single-engine

Eurocopter EC120 Colibri

Eurocopter EC120 Colibri F-HBKB Heli Dax

The Eurocopter (now Airbus Helicopters) EC120 Colibri (English: hummingbird) is a 5-seat, single-engine, single main rotor, light helicopter.

  • Role: Light utility helicopter
  • National origin: France
  • Manufacturer: Eurocopter/Airbus Helicopters/Harbin Aircraft Industry Group
  • First flight: 9 June 1995
  • Introduction: 1998
  • Status: In service
  • Produced: 1995 – present
  • Number built: 550+

Specifications (EC120 B)

General characteristics

  • Crew: 1 or 2 pilots
  • Capacity: 4 passengers
  • Length: 9.6 m (31 ft 5 in)
  • Rotor diameter: 10.0 m (32 ft 8 in)
  • Height: 3.4 m (11 ft 2 in)
  • Empty weight: 991 kg (2,185 lb)
  • Useful load: 724 kg (1,596 lb)
  • Max. takeoff weight: 1,715 kg (3,781 lb)
  • Powerplant: 1 × Turbomeca Arrius 2F turboshaft, 376 kW (504 shp)

Performance

  • Never exceed speed: 278 km/h (150 knots, 172 mph)
  • Cruise speed: 223 km/h (120 knots, 138 mph)
  • Range: 710 km (383 nm, 440 mi)
  • Service ceiling: 5,182 m (17,000 ft)
  • Rate of climb: 5.84 m/s (1,150 ft/min)

Avionics
Vehicle and Engine Multifunction Display (VEMD) with First Limit Indicator (FLI) fitted as standard.

Arado Ar 96

Arado Ar 96 B-1 U-CF Luftwaffe

The Arado Ar 96 was a German single-engine, low-wing monoplane of all-metal construction military trainer produced by Arado Flugzeugwerke.

  • Role: Military Trainer
  • National origin: Germany
  • Manufacturer: Arado Flugzeugwerke
  • First flight: 1938
  • Introduction: 1939
  • Status: 2 aircraft in museums
  • Number built: ca 3,500

Operators

  • Bulgarian Air Force
  • Czechoslovakian Air Force
  • French Air Force (Postwar)
  • Luftwaffe
  • Hungarian Air Force
  • Romanian Air Force
  • Slovenské vzdušné zbrane

Arado Ar 96 B-1 U-CF Luftwaffe

Survivors

Specifications (Arado Ar 96B-2)

General characteristics

  • Crew: 2
  • Length: 9.1 m (29 ft 10 in)
Ar 396A-1: 9.3 m (31 ft)
  • Wingspan: 11 m (36 ft 1 in)
  • Height: 2.6 m (8 ft 6 in)
Ar 396A-1: 2.45 m (8 ft)
  • Wing area: 17.1 m2 (184 sq ft)
Ar 396A-1: 18.3 m2 (197 sq ft)
  • Empty weight: 1,295 kg (2,855 lb)
Ar 396A-1: 1,643 kg (3,622 lb)
  • Max takeoff weight: 1,700 kg (3,748 lb)
Ar 396A-1: 2,060 kg (4,542 lb)
  • Powerplant: 1 × Argus As 410A-1 inverted V-12 air-cooled piston engine, 347 kW (465 hp)
Ar 396A-1: 1 x 433 kW (581 hp) Argus As 411MA inverted V-12 air-cooled piston engine
  • Propellers: 2-bladed variable pitch metal propeller

Performance

  • Maximum speed: 330 km/h (205 mph; 178 kn) at sea level
  • Cruising speed: 295 km/h (183 mph; 159 kn)
Ar 396A-1: 275 km/h (171 mph) at sea level
  • Range: 990 km (615 mi; 535 nmi)
Ar 396A-1: 600 km (373 mi)
  • Service ceiling: 7,100 m (23,294 ft)
Ar 396A-1: 6,900 m (22,638 ft)
  • Rate of climb: 5.083 m/s (1,000.6 ft/min)
  • Time to altitude:
Ar 396A-1: 4,000 m (13,123 ft) in 10 minutes 18 seconds
Armament

1 × 7.92 mm (0.312 in) MG 17 machine gun

Ar 396A-1: 1 × 7.92 mm (0.312 in) MG 17 machine gun + 2 x 50 kg (110 lb) bombs on underwing racks

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-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)

Dassault Mirage III

Dassault Mirage IIIDS HB-RDF/J-2012

The Dassault Mirage III is a family of single-seat, single-engine, fighter aircraft produced by Dassault Aviation for the French Air Force and widely exported.

  • Role: Interceptor aircraft
  • National origin: France
  • Manufacturer: Dassault Aviation
  • First flight: 17 November 1956
  • Introduction: 1961
  • Status: In service only by Pakistan Air Force
  • Produced: 1977–1983
  • Number built: 1,422
  • Variants: Dassault Mirage IIIV (BalzacV), Dassault Mirage 5, Atlas Cheetah

Dassault Mirage IIIS J-2313 Swiss Air Force

Military operators

  • Argentinian Air Force
  • Egyptian Air Force

Former military operators

  • Abu Dhabi Air Force
  • Royal Australian Air Force
  • Belgium Air Force
  • Brazilian Air Force
  • Chilean Air Force
  • Colombian Air Force
  • French Air Force
  • Gabonese Air Force
  • Israeli Air Force
  • Lebanese Air Force
  • Libyan Air Force
  • Peruvian Air Force
  • South-African Air Force
  • Spanish Air Force
  • Swiss Air Force
  • Venezuelan Air Force
  • Zairian Air Force

Dassault Mirage IIIDS HB-RDF/J-2012

Specifications (Mirage IIIE)

General characteristics

  • Crew: 1
  • Length: 15.03 m (49 ft 3½ in)
  • Wingspan: 8.22 m (26 ft 11⅝ in)
  • Height: 4.50 m (14 ft 9 in)
  • Wing area: 34.85 m² (375 ft²)
  • Empty weight: 7,050 kg (15,600 lb)
  • Loaded weight: 9,600 kg (21,164 lb)
  • Max. takeoff weight: 13,700 kg (30,203 lb)
  • Powerplant: 1 × SNECMA Atar 09C turbojet
    • Dry thrust: 41.97 kN (9,436 lbf)
    • Thrust with afterburner: 60.80 kN (13,668 lbf)

Performance

  • Maximum speed: Mach 2 (2,350 km/h, 1,268 knots, 1,460 mph) at 12,000 m (39,370 ft)
  • Combat radius: 1,200 km (647 nmi, 746 mi)
  • Ferry range: 3,335 km ()
  • Service ceiling: 17,000 m (55,775 ft)
  • Rate of climb: 46,600 ft/min ()

Armament

  • Guns: 2× 30 mm (1.18 in) DEFA 552 cannons with 125 rounds per gun
  • Rockets: 2× Matra JL-100 drop tank/rocket pack, each with 19× SNEB 68 mm rockets and 66 US gallons (250 liters) of fuel
  • Missiles: 2× AIM-9 Sidewinders OR Matra R550 Magics plus 1× Matra R530,
  • Bombs: 4,000 kg (8,800 lb) of payload on five external hardpoints, including a variety of bombs, reconnaissance pods or Drop tanks; French Air Force IIIEs through 1991, equipped for AN-52 nuclear bomb.

BAE Systems Hawk

British Aerospace Hawk 51 HW-334 3 Finnish Air Force

The BAE Systems Hawk is a British single-engine, jet-powered advanced trainer aircraft. A derivative of the Hawk was selected by the United States Navy as their new trainer aircraft. Designated the McDonnell Douglas T-45 Goshawk. The most famous users of the Hawk are the Red Arrows aerobatic team, who adopted the plane in 1979.

  • Role: Advanced jet trainer and light attack aircraft
  • Manufacturer: BAE Systems
  • National origin: United Kingdom
  • First flight: 21 August 1974
  • Introduction: 1976
  • Produced: 1974–present
  • Number built: 1,000+
  • Status: In service

Military operators

  • Royal Australian Air Force – 33 Hawk 127
  • Royal Bahraini Air Force – 6 Hawk 129
  • Royal Canadian Air Force – 16 Hawk 115
  • Finnish Air Force – 75 Hawks (50 Mk.51, 7 Mk.51A, 18 Mk.66
  • Indian Air Force – 66 Hawk 132 (total 106 ordered for IAF)
  • Indian Navy – 8 Hawk 132 (total 17 ordered)
  • Indonesian Air Force – 38 Hawk 53/109/209
  • Kuwait Air Force – 10 Hawk 64
  • Royal Malaysian Air Force – 19 Hawk 108/208
  • Royal Air Force of Oman – 15 Hawk 103/203
  • Royal Saudi Air Force – 45 Hawk 65
  • South African Air Force – 24 Hawk 120
  • Royal Air Force – 81 Hawk T1/28 Hawk T2
  • Royal Navy – 17 Hawk T1
  • United Arab Emirates Air Force – 36 Hawk 61/63/102

Former operators

  • Kenya Air Force – 7 Hawk 52, out of service and retired as of 2012
  • Republic of Korea Air Force introduced 20 T-59 (Hawk 67) in September 1992. Retired from service in 2013
  • Swiss Air Force: 20 Hawk Mk. 66 were bought in 1992 but decommissioned in 2002, of which 18 were sold to Finland in June 2007
  • Air Force of Zimbabwe – 12 Hawk 60 retired as of 2011 because of lack of spares and lack of BAE support

Specifications (Hawk 128)

General characteristics

  • Crew: 2: student, instructor
  • Length: 12.43 m (40 ft 9 in)
  • Wingspan: 9.94 m (32 ft 7 in)
  • Height: 3.98 m (13 ft 1 in)
  • Wing area: 16.70 m2 (179.64 ft2)
  • Empty weight: 4,480 kg (9,880 lb)
  • Useful load: 3,000 kg (6,600 lb)
  • Max takeoff weight: 9,100 kg (20,000 lb)
  • Powerplant: 1× Rolls-Royce Adour Mk. 951 turbofan with FADEC, 29 kN (6,500 lbf) 29 kN

Performance

  • Maximum speed: Mach 0.84 (1,028 km/h, 638 mph) at altitude
  • Range: 2,520 km (1,360 nmi, 1,565 mi)
  • Service ceiling: 13,565 m (44,500 ft)
  • Rate of climb: 47 m/s (9,300 ft/min)
  • Thrust/weight: 0.65

Armament

Note: all armament is optional.
  • 1× 30 mm ADEN cannon, in centreline pod
  • Up to 6,800 lb (3,085 kg) of weapons on five hardpoints, including:
    • 4× AIM-9 Sidewinder or ASRAAM on wing pylons and wingtip rails
  • 1,500 lb (680 kg), limited to one centreline and two wing pylons (Hawk T1)

Eurocopter EC120 Colibri

Eurocopter EC120 F-HBKB French Army

The Eurocopter (now Airbus Helicopters) EC120 Colibri (English: hummingbird) is a 5-seat, single-engine, single main rotor, light helicopter. Jointly designed and developed by Eurocopter, China National Aero-Technology Import & Export Corporation (CATIC), Harbin Aviation Industries (Group) Ltd (HAIG) and Singapore Technologies Aerospace Ltd (STAero) at Eurocopter France’s Marignane facility, the EC120 B is assembled by Eurocopter in France and Australia.

  • Role: Light utility helicopter
  • National origin: France, China, Singapore
  • Manufacturer: Eurocopter/Airbus Helicopters, Harbin Aircraft Industry Group
  • First flight: 9 June 1995
  • Introduction: 1998
  • Status: In service
  • Produced: 1995-present
  • Number built: over 550

Military operators

  • People’s Liberation Army Air Force (China)
  • Hélidax (Army Aviation Training) (France)
  • Indonesian Air Force
  • Indonesian Navy
  • Republic of Singapore Air Force
  • Spanish Air Force

Specifications (EC120 B)

General characteristics

  • Crew: 1 or 2 pilots
  • Capacity: 4 passengers
  • Length: 9.6 m (31 ft 5 in)
  • Rotor diameter: 10.0 m (32 ft 8 in)
  • Height: 3.4 m (11 ft 2 in)
  • Empty weight: 991 kg (2,185 lb)
  • Useful load: 724 kg (1,596 lb)
  • Max. takeoff weight: 1,715 kg (3,781 lb)
  • Powerplant: 1 × Turbomeca Arrius 2F turboshaft, 376 kW (504 shp)

Performance

  • Never exceed speed: 278 km/h (150 knots, 172 mph)
  • Cruise speed: 223 km/h (120 knots, 138 mph)
  • Range: 710 km (383 nm, 440 mi)
  • Service ceiling: 5,182 m (17,000 ft)
  • Rate of climb: 5.84 m/s (1,150 ft/min)

Avionics
Vehicle and Engine Multifunction Display (VEMD) with First Limit Indicator (FLI) fitted as standard.

Pilatus PC-9

Pilatus PC-9 HB-HPJ Pilatus Aircraft

The Pilatus PC-9 is a single-engine, low-wing tandem-seat turboprop training aircraft manufactured by Pilatus Aircraft of Switzerland.

  • Role: Advanced Trainer aircraft
  • Manufacturer: Pilatus Aircraft
  • Designer: Pilatus Aircraft
  • First flight: 7 May 1984
  • Introduction: 1984 – present
  • Status: Active service
  • Number built: 265
  • Developed from: Pilatus PC-7
  • Developed into: T-6 Texan II

Pilatus PC-9 HB-HPJ Demo Pilatus Aircraft

Military operators

  • Royal Australian Air Force
  • Bulgarian Air Force
  • Croatian Air Force
  • Chadian Air Force
  • Cyprus Air Forces
  • Irish Air Corps
  • Mexican Air Force
  • Myanmar Air Force
  • Royal Air Force of Oman
  • Royal Saudi Air Force
  • Slovenian Air Force and Air Defence
  • Swiss Air Force
  • Royal Thai Air Force

Former military operators

  • National Air Force of Angola
  • Luftwaffe
  • United States Army

Pilatus PC-9 HB-HPJ Demo Pilatus Aircraft

Specifications (PC-9M)

General characteristics

  • Crew: one or two pilots
  • Length: 10.14 m (33 ft 3 in)
  • Wingspan: 10.125 m (33 ft 3 in)
  • Height: 3.26 m (10 ft 8 in)
  • Wing area: 16.29 m2 (175.3 sq ft)
  • Empty weight: 1,725 kg (3,803 lb)
  • Gross weight: 2,350 kg (5,181 lb)
  • Max takeoff weight: 3,200 kg (7,055 lb)
  • Powerplant: 1 × Pratt & Whitney Canada PT6A-62 turboprop, 857 kW (1,149 hp) flat-rated at 708 kW (950 shp)

Performance

  • Maximum speed: 593 km/h (368 mph; 320 kn)
  • Cruising speed: 556 km/h (345 mph; 300 kn) at 7,620 m (25,000 ft)
  • Stall speed: 143 km/h (89 mph; 77 kn) EAS flaps and gear up, 128 km/h (80 mph; 69 kn) flaps and gear down
  • Range: 1,537 km (955 mi; 830 nmi)
  • Endurance: 4 hr 30 min
  • Service ceiling: 11,580 m (37,992 ft)
  • g limits: + 7.0 g to −3.5 g
  • Rate of climb: 20.8 m/s (4,090 ft/min)
  • Take-off distance over 50 ft (15 m) obstacle at sea level: 1,280 ft (391 m)
  • Landing distance over 50 ft (15 m) obstacle at sea level: 2,295 ft (700 m)

Armament

  • Hardpoints: Three hardpoints under each wing, inner two rated at 250 kg (550 lb), outer rated at 110 kg (240 lb)

Pilatus PC-9 C-406 Zielflugstaffe Swiss Air Force