General view of the single engined 14.2 H.P. aircraft E-12n  

  • Fundamental technical flight characteristics of aircraft E -12n (for pilots with weight above 80 kGs recommended engines are Hirth F-33 European manufactorer (28 h.p.), or from from American Hirth Dealer, or Simonini Mini-2Plus (28 h.p.). Maximum take-off weight 160 kGs).

  • Engine Raket-120 Aero (better perfomance can be achieved with Simonini Mini-4)
  • Redrive and muffler are regular R-120A
  • Length of fuselage, mm 4450
  • Wingspan , mm 6500
  • Wingload, kg/sq.m 23-27
  • Wing area, square meter 5,38 (variants up to 5.8)
  • Maximum takeoff weight, kg 140 (variants up to 160)
  • Empty weight , kg 45-48 (up to 65 kGs with other engines)
  • Pilot`s weight, kg 65-90 (up to 95)
  • Engine power, hp.14,2
  • Propeller diameter, mm 1280
  • Propeller thrust, static- 45 kg     (-at speed V=83 km/h -33 kg)
  • Fuel tank - 6 l
  • Fuel consumption -4 l per 100 km
  • Take-off speed, km/h 65
  • Landing speed, km/h 62
  • Stalling speed, km/h -59
  • Cruising speed, km/h -80-90
  • Vne, km/h -140
  • Max. speed, km/h -100
  • Rate of climb, m/s    (within weight of the pilot 65-90kg) - 3,2 -2,2
  • Permissible wind - 8m/s
  • Take-off run - 60-90m m
  • Service ceiling 2500 m (7500 ft)


    Other characteristics E -12n

  • Thrust-weight ratio- weight/kg at thrust/kg in the climb within MTOW 120kg of ------3.63 kg/kg
  • Thrust-weight ratio within MTOW 140kg - 4.52kg/kg (some 25% worse).
  • For the comparison Cri-Cri does have 4,47 kg/kg    (as much as E -12 with MTOW 140 kg)!
  • The steady-state (static) stability:Ahs=0,37"   Bvs=0,04
  • Maneuverability, the coefficient of lateral stability Mx=0.0115.
  • These figures are sufficient for the nonmaneuverable aircraft.(maneuverable aircraft for the aerobatics).



  • Wing airfoil --------------- P-III-18%.
  • Wing chord ------------ 880 mm
  • Area of the aileron ----------- 0,2 sq.m.
  • Aileron span -------------- 980mm
  • Aileron chord ---------------- 210 mm
  • CofG at ---------- 26% (229mm from the leading edge of an airfoil profile)
  • Permissible centering of ----- 22% - 29%.
  • Change in the centering with the pilot of 60kg and 90kg of ----- 0,4%.

  • Horizontal stabilizer span ----- 1500 mm
  • HS chord ----- 500mm
  • HS airfoil -------- symmetrical 6% thikness, simplified
  • HS area -------- 0.75 sq.m.
  • VS area -------- 0.52 sq.m.
  • Angles of deflection for controls VS and HS ----- 20° (upward and downward)
  • Aileron angles, downward 17° (+_2),      upward 22° (+ -2)
  • Motion of the nain gear spring with load change from 0 to max. calculated..- 150 mm
  • Calculated vertical impact velocity by chassis -2,2 m/s
  • Operational overloads of aircraft - +4 g -(-2,5) g

  • Balance data and units weight are cited in the CofG balance table.
  • Chassis of aircraft and relatively low take-off speed makes it possible to operate the aircraft
        from ground runways, namely from the usual clearings and grass fields, where the height of the vegetation does not exceed 200mm.
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