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Beaujon Mach .07

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Beaujon Mach .07

Mach .07
Role Ultralight aircraft
National origin United States
Manufacturer Beaujon Aircraft
Designer Herbert Beaujon
Status Plans available

The Beaujon Mach .07 is a single-seat, American high-wing, tractor configuration ultralight aircraft. The aircraft is available as plans from Beaujon Aircraft of Ardmore, Oklahoma.[1][2]

Development

Designed by Herbert Beaujon, the Mach .07 is named for its top speed of 48 mph (77 km/h). Beaujon Aircraft publishes the plans along with six other designs in book form under the name How to Build Ultralights.[1]

The Mach .07 was specifically designed to comply with the United States ultralight category and its FAR 103 Ultralight Vehicles rules, including the category's maximum 254 lb (115 kg) empty weight.[1][2]

With the specified 50 lb (23 kg) 250 cc Zenoah G-25 22 hp (16 kW) powerplant the aircraft has an empty weight of 160 lb (73 kg).[1]

Reviewer Andre Cliche says:

Design

The aircraft's wing and tail structure are built from aluminum and are covered in aircraft fabric. The wing is strut-braced. The Mach .07 uses no structural cables in its construction. The conventional landing gear features a steerable tail wheel attached to the rudder.[1]

The controls are two-axis, with a side-stick that laterally activates the rudder to induce roll and which longitudinally activates the elevator for pitch control. No rudder pedals are installed and the wing construction is greatly simplified by the elimination of ailerons.[1]

The open frame fuselage consists of 6061T6 aluminum tubing and a single open pilot's seat. The powerplant is installed at the front end of the aircraft tailboom tube, above the pilot. Standard fuel capacity is 2.5 US gal (9 l).[1]


Specifications (Mach .07)

Data from Cliche[1]

General characteristics
  • Crew: one
  • Capacity: no passengers
  • Length: ()
  • Wingspan: ()
  • Height: ()
  • Empty weight: 160 lb (73 kg)
  • Useful load: 240 lb (109 kg)
  • Max. takeoff weight: 400 lb (181 kg)
  • Powerplant: 1 × Zenoah G-25 250 cc two-stroke fixed pitch, 22 hp (16 kW)
  • Propellers: 1 propeller, 1 per engine

Performance

See also

Aircraft of comparable role, configuration and era

References

External links

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