2 thoughts on “Nanchang CJ6G-Yak-18A

  1. Randy DeVere

    The CJ-6 (translation 初教 or CJ = 初级教练机 or Chuji Jiaolianji = Primary Trainer in English) is said to be an all-original Chinese design but may be an improved copy of the Yak 18A. Its predecessor, the Nanchang CJ-5, was a license-built version of the Yak-18. However, advancements in pilot training brought a need for a new aircraft with improved performance and a tricycle landing gear. When the Soviet Union developed the Yak-18A, PLAAF engineers decided that its performance and design would not suit China’s needs.

    During late 1957 Aeronautical Engineers Cheng Bushi and Lin Jiahua began work in Shenyang on a trainer design that addressed the shortcomings of the Yak-18A. The design they delivered featured an aluminum semi-monocoque fuselage, flush-riveted throughout, and introduced a modified Clark airfoil wing design with pronounced dihedral in the outer sections. Wind tunnel testing validated the design, and in May 1958 the program was transferred to the Nanchang Aircraft Manufacturing factory where Chief Engineer Goa Zhenning initiated production of the CJ-6. The first flight of the CJ-6 was completed on August 27, 1958 by Lu Maofan and He Yinxi. Over 2,000 have been built and it is still in use today as the Primary Trainer for the Chinese Military

    One thing to note is that the Nanchang CJ-6 makes extensive use of pneumatics to control the gear and flap extension/retraction, operate the brakes and start the engine. An engine-driven air pump recharges the system, however if air pressure is too low to start the engine then the onboard air tank can be recharged by an external source.

    General characteristics
    (Numbers are for this modified model, numbers in ( ) are stock CJ6A)
    • Crew: …………………………………Two (student & instructor)
    • Length: ………………………………27 ft 9 in
    • Wingspan: ……………………………33 ft 6 in
    • Height: ……………………………….10 ft 8 in
    • Empty weight: ……………………….2,274 (2,414 lb)
    • Max. takeoff weight: ………………………3,400 CJ6-G (3,086 lb)
    • Power plant: …………………………M14P 360HP (Housai 285 hp)
    Performance
    • Never exceed speed: …………………370 km/h (200 kts, 230 mph)
    • High Cruise Speed:………………..…146Kts True (138 kts)
    • Normal Cruise Speed: ……………….139Kts (135 kts)
    • Stall Speed:………………………..….54 kts (52 kts)
    • Maximum speed: ……………………160 kts, 185 mph)
    • Range: ……………………………….642 nm with 30 min reserve (372 nmi)
    • Service ceiling: ………………………>20,500+ ft
    • Rate of Climb: ………………………1,700+ ft/min (700 ft/min)
    • G Limit: …………………………….+6 / -3 G
    Armament
    • 2 x 7.62mm machine guns
    • Weapons stations and hard points under the wings
    • Bombs
    • Rocket launchers
    Operating Costs (Real/Actual at 100 hours a year)
    • Just fuel and oil: ………………………..$81.50 / Hour
    • Fuel, Oil, Oil changes: …………………$83.23 / Hour
    • Above Plus Insurance, Annual: …..…….$126.50 / Hour
    • Above plus engine/prop @ 2k hours: …..$139.73 / Hour

    Reply
  2. Randy DeVere

    Engine: M14P
    The Vedeneyev M14P is a Russian nine cylinder, four-stroke, air-cooled, petrol-powered radial engine. Producing 360 hp (268 kW), its design dates from the 1940s, and is itself a development of the Ivchenko AI-14 engine. The M14P has recently become increasingly popular in experimental aircraft and kit designs such as the Murphy Moose, Radial Rocket, Pitts Model 12, and others. Historically, the engine has been used extensively by the Yakovlev and Sukhoi Design Bureaus.
    General characteristics
    • Type: Nine cylinder, four-stroke, air-cooled radial engine
    • Displacement: 10.2 L ( ~ 622 cubic inches )
    • Diameter: 985 ± 3 mm ( ~ 39 inches )
    • Dry weight: 214 kg (472 lb)

    Reply

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