JEROEN VOGELAAR: Aviation Photographs

STOL

Fieseler Fi 156 Storch

Fieseler Fi-156C-3 Storch F-AZRA/2E+RA Luftwaffe

The Fieseler Fi 156 Storch was a small German liaison aircraft built by Fieseler before and during World War II. It remains famous to this day for its excellent STOL (Short-Take-Off-and-Landing) performance.

  • Role: Reconnaissance & communications
  • National origin: Germany
  • Manufacturer: Fieseler/Morane-Saulnier
  • First flight: 24 May 1936
  • Introduction: 1937
  • Status: Privately owned, or in museums
  • Retired: Germany: 1945, France: 1970
  • Produced: 1937–1949 (1965 for the MS 500)
  • Number built: Over 2,900

Production per factory

  • Fieseler: 1.908
  • Morane-Saulnier: 784
  • Mraz: 78
  • Leichtbau: 73

Military operators

  • Bulgarian Air Force
  • Royal Khmer Air Force (Post war) and Khmer National Air Force
  • Air Force of the Independent State of Croatia
  • Czechoslovakian Air Force (Post war)
  • Egyptian Air Force
  • Finnish Air Force
  • French Air Force (Post war)
  • French Navy (Post war)
  • French Army (Post war)
  • Luftwaffe German Air Force)
  • Greek Air Force (Post war)
  • Royal Hungarian Air Force
  • Regia Aeronautica (Italian Air Force)
  • Royal Lao Air Force (Post war)
  • Royal Moroccan Air Force (Post war)
  • Royal Norwegian Air Force (Post war)
  • Polish Air Force (Post war)
  • Polish Navy (Post war)
  • Royal Romanian Air Force
  • Romanian Air Force (Post war)
  • Slovak Air Force (1939–1945)
  • Vietnam Air Force (Post war)
  • Soviet Air Force
  • Spanish Air Force
  • Royal Swedish Air Force
  • Swiss Air Force
  • Royal Air Force
  • Yugoslav Royal Air Force
  • SFR Yugoslav Air Force

Specifications (Fi 156)

General characteristics

  • Crew: 2
  • Length: 9.9 m (32 ft 6 in)
  • Wingspan: 14.3 m (46 ft 9 in)
  • Height: 3.1 m (10 ft 0 in)
  • Wing area: 26 m² (280 ft²)
  • Empty weight: 860 kg (1,900 lb)
  • Loaded weight: 1,260 kg (2,780 lb)
  • Powerplant: 1 × Argus As 10 air-cooled inverted V8 engine, 180 kW (240 hp)

Performance

  • Maximum speed: 175 km/h (109 mph) at 300 m (1,000 ft)
  • Range: 380 km (210 nmi, 240 mi)
  • Service ceiling: 4,600 m (15,090 ft)
  • Rate of climb: 4.8 m/s (945 ft/min)
  • Wing loading: 48.5 kg/m² (9.9 lb/ft²)
  • Power/mass: 143 W/kg (0.087 hp/lb)

Armament

  • Guns: MG 15 machine gun

Pilatus PC-6 Porter/Turbo-Porter

Pilatus PC-6B1-H2 Turbo Porter HB-FCF Swiss Air Force

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

  • AU-23A Peacemaker – Armed gunship, counter-insurgency, utility transport version for the U.S. Air Force
  • UV-20A Chiricahua – STOL utility transport version for the U.S. Army

Civil Pilatus PC-6 Porter/Turbo-Porter

Military operators

  • National Air Force of Angola
  • Argentine Navy
  • Gendarmeria Nacional Argentina
  • Austrian Air Force
  • Myanmar Air Force
  • Chad Air Force
  • Ecuadorian Army
  • Islamic Republic of Iran Air Force
  • Mexican Air Force
  • Peruvian Air Force
  • Slovenian Air Force and Air Defence
  • Swiss Air Force
  • Royal Thai Air Force
  • United States Army

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)

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)

Dornier Do 228

Donier 228-200 PH-CGN Kustwacht

  • Role: twin-turboprop STOL utility aircraft
  • National origin: Germany
  • Manufacturer: Dornier GmbH/RUAG Aviation
  • First flight: March 21, 1981
  • Introduction: 1982
  • Status: In service
  • Produced: 1981-1998 and 2009–present
  • Number built: 284

Specifications (Do 228-212)

General characteristics

  • Crew: two pilots
  • Capacity: 19 passengers
  • Payload: 2,340 kg freight (5,158 lb)
  • Length: 16.56 m (54 ft 4 in)
  • Wingspan: 16.97 m (55 ft 8 in)
  • Height: 4.86 m (15 ft 11 in)
  • Wing area: 32.0 m² (344 sq ft)
  • Airfoil: A-5
  • Empty weight: 3,739 kg (8,243 lb)
  • Max. takeoff weight: 6,400 kg (-212) 6,200 kg (-202K) 6,100 kg (-202) 5,700 (-101) (14,550 lb)
  • Powerplant: 2 × Garrett AiResearch TPE-331-5-252D or -10 variation( GP and GT ) turboprop, 578 kW (776 shp flat rated for -5A and -10 powerplants Available at 30 Celsius at Sea Level / 715 shp flat rated for -5 variations) each
  • Propellers: Hartzell Propellers model- HC-B4TN-5ML/LT10574 , 4 per engine
    • Propeller diameter: 105 in ()

Performance

  • Never exceed speed: 223 Knots (-212 )
  • Maximum speed: 223 knots (-212) 200 Knots(-200)
  • Cruise speed: 190 knots (196 mph) at appox 15 degree C with 85% torque
  • Stall speed: Flaps dependent () Appox. 75 flaps Down
  • Range: 1,111 km (715 nmi, 823 mi) with full payload
  • Service ceiling: 8,535 m (28,000 ft)
  • Rate of climb: 7.5 m/s (1,870 ft/min)