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The Kamov Ka-26 (NATO reporting name Hoodlum) is a Soviet light utility helicopter with co-axial rotors.

Ka-26
Kamov Ka-26, RA-24308 (remix).jpg
A Kamov Ka-26 in flight
Role Light utility
Manufacturer Kamov
First flight 18 August 1965
Introduction 1969
Status Active
Produced 1969–1985
Number built 816
Developed into Kamov Ka-126
Kamov Ka-226

Contents

DevelopmentEdit

The Ka-26 entered production in 1969. 816 have been built. A variant with a single turboshaft engine is the Ka-126. A twin turboshaft-powered version is the Ka-226. (All the Ka-26/126/128/226 variants are code-named by NATO as "Hoodlum").

DesignEdit

The fuselage of the Ka-26 consists of a fixed, bubble-shaped cockpit containing the pilot and co-pilot, plus a removable, variable box available in medevac, passenger-carrying and crop duster versions. The helicopter can fly with or without the box attached for flexibility. It is powered by two 325 hp (239 kW) Vedeneyev M-14V-26 radial engines mounted in outboard nacelles.

The Ka-26 is small enough to land on a large truck bed. The reciprocating engines are more responsive than turboshafts but require more maintenance. It runs mostly at 95% power in crop dusting with usually excess payload, leaving little reserve power for emergencies. Due to frequent overloads, the interconnect shaft joining the two engines is prone to breakage and requires frequent inspection.

The standard instrumentation of the Ka-26, like larger naval Kamovs, may be overkill for civilian or crop dusting use. The 18-dials cockpit panel masks a part of the right-downwards view, needed to avoid telephone and power lines at low altitudes. The instrument panel may be simplified to retain the six main dials. As there is a low rotor clearance at the aircraft front, it is approached from the rear when the rotors are turning.

Due to the limitations of the Ka-26, USSR and Romania agreed under the Comecon trade to build a single-engine version, the Kamov Ka-126, with better aerodynamics and range.

Operational historyEdit

The Ka-26 was used by some Warsaw Pact armies in the light paratroop or airborne role,[citation needed] but its slow (150 km/h) cruise speed compared with the Mil-2 (220 km/h) limits its military use. However, its shorter length (7.75 m) compared with the Mil Mi-2 (11.9 m) and smaller rotor diameter (13 m vs. 14.6 m) are advantageous when operating in an urban area. It has a longer range than the Mil-2 as well. The Ka-26 is eminently useful for crop dusting. The coaxial main rotor configuration, which makes the Ka-26 small and agile, also results in a delicate airflow pattern under the helicopter, providing a thorough, yet mild distribution of chemicals onto plants. The Ka-26 is often used to spray grape farms in Hungary, where conventional "main rotor and tail rotor" layout helicopters would damage or up-root the vine-stocks with their powerful airflow.[citation needed] Hungarian Kamov operators claim that coaxial rotors of the Ka-26 creates an airflow which allows pesticides to settle underneath, rather than on top of, the leaves, this means a much more effective distribution of pesticides, as most pests and parasites do not live on the top side of foliage. Additionally, the coaxial vortex system is symmetrical, allowing the distribution of the pesticide to be more uniform.

VariantsEdit

Ka-26 Hoodlum-A
One or two crew utility light helicopter, powered by two 325-hp (239-kW) VMK (Vedeneyev) M-14V-26 radial engines. 850 built.
Ka-26SS
NOTAR technology testbed for the Ka-118 fitted with tail jet beams.
Ka-126 Hoodlum-B
One or two crew utility light helicopter, powered by one 720-shp (537-kW) OMKB "Mars" (Glushenkov) TVD-100 turboshaft engine. First flown in 1986, built and developed by Industria Aeronautică Română in Romania. 2 prototypes and 15 series helicopter built.
V-60
A prototype light armed escort helicopter based on the Ka-126.
Ka-128
One prototype, powered by a 722-shp (538-kW) Turbomeca Arriel 1D1 turboshaft engine.
Kamov Ka-226
Six or seven seat utility helicopter, powered by two 450-shp (335-kW) Rolls-Royce (Allison ) 250-C20R/2 turboshaft engines.

OperatorsEdit

Specifications (Ka-26)Edit

 
The 325-hp (239-kW) VMK (Vedeneyev) M-14V-26 radial engine of the Ka-26

Data from Jane's All The World's Aircraft 1982–83 [10]

General characteristics

  • Crew: 2
  • Capacity: 6 passengers (cargo/passenger pod)
  • Payload: 900 kg (1,985 lb) (chemical hopper)
    • 1,100 kg (2,425 lb) (flying crane)
  • Length: 7.75 m (25 ft 5 in)
  • Rotor diameter: 2x 13.00 m (42 ft 8 in)
  • Height: 4.05 m (13 ft 3½ in)
  • Disc area: 265.5 m² (2,856 ft²)
  • Empty weight: 1,950 kg (4,300 lb)
  • Max. takeoff weight: 3,250 kg (7,170 lb)
  • Powerplant: 2 × Vedeneyev M-14 V-26 radial piston engines, 239 kW (325 hp) each

Performance

See alsoEdit

Related development

Aircraft of comparable role, configuration and era

ReferencesEdit

  1. ^ "Gazpromavia – fleet". gazpromavia.ru. Retrieved 10 March 2013.
  2. ^ "West Copter "about us"". westcopter.ro. Retrieved 10 March 2013.
  3. ^ "World Air Forces 1987 pg. 44". flightglobal.com. Retrieved 10 March 2013.
  4. ^ "Bulgarski voennovazdushni sili Ka-26". Retrieved 10 March 2013.
  5. ^ World Air Forces – Historical Listings Mongolia (MON) Archived 2012-09-05 at the Wayback Machine. worldairforces.com. Retrieved on 2013-08-27.
  6. ^ "Valstybes Sienos Apsaugos TarnybaLa-26". Retrieved 10 March 2013.
  7. ^ "World's Air Forces 1981 pg. 346". flightglobal.com. Retrieved 10 March 2013.
  8. ^ "Magyar Légiero Ka-26". Retrieved 10 March 2013.
  9. ^ "Kamov Ka-26 in Sri Lanka Air Force". Retrieved 16 October 2016.
  10. ^ Taylor 1982, pp. 204–205.

External linksEdit