| 词条 | Beaujon Mach .07 | |||||||||||||||
| 释义 |
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] DevelopmentDesigned by Herbert Beaujon, the Mach .07 is named for its top speed of {{convert|48|mph|km/h|0|abbr=on}}. 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 {{convert|254|lb|kg|0|abbr=on}} empty weight.[1][2] With the specified {{convert|50|lb|kg|0|abbr=on}} 250 cc Zenoah G-25 {{convert|22|hp|kW|0|abbr=on}} powerplant the aircraft has an empty weight of {{convert|160|lb|kg|0|abbr=on}}.[1] Reviewer Andre Cliche says: {{cquote|The Mach .07 is a beautifully simple ultralight which is reminiscent of the early designs that gave rise to the ultralight phenomenon in the late 70s.[1] }}DesignThe 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 {{convert|2.5|USgal|l|0|abbr=on}}.[1] Specifications (Mach .07){{aircraft specifications|plane or copter?=plane |jet or prop?=prop |ref=Cliche[1] |crew=one |capacity= no passengers |payload main= |payload alt= |payload more= |length main= |length alt= |span main= |span alt= |height main= |height alt= |area main= |area alt= |airfoil= |empty weight main= 160 lb |empty weight alt= 73 kg |loaded weight main= |loaded weight alt= |useful load main= 240 lb |useful load alt= 109 kg |max takeoff weight main= 400 lb |max takeoff weight alt= 181 kg |max takeoff weight more= |more general= |engine (jet)= |type of jet= |number of jets= |thrust main= |thrust alt= |thrust original= |afterburning thrust main= |afterburning thrust alt= |thrust more= |engine (prop)= Zenoah G-25 250 cc two-stroke |type of prop= fixed pitch |number of props=1 |power main= 22 hp |power alt=16 kW |power original= |power more= |propeller or rotor?=propeller |propellers=1 |number of propellers per engine= 1 |propeller diameter main= |propeller diameter alt= |max speed main= 48 mph |max speed alt=78 km/h |max speed more= |cruise speed main= 38 mph |cruise speed alt=62 km/h |cruise speed more |stall speed main= 20 mph |stall speed alt= 32 km/h |stall speed more= |never exceed speed main= |never exceed speed alt= |range main= |range alt= |ferry range main= |ferry range alt= |ferry range more= |ceiling main= |ceiling alt= |climb rate main= 350 ft/min |climb rate alt= 1.7 m/s |loading main= |loading alt= |thrust/weight= |power/mass main=18.2 lb/hp |power/mass alt=0.09 kW/kg |more performance= |armament= |guns= |bombs= |rockets= |missiles= |hardpoints= |hardpoint capacity= |avionics= }} See also{{aircontent|see also= |related= |similar aircraft=
|lists= }} References1. ^1 2 3 4 5 6 7 8 Cliche, Andre: Ultralight Aircraft Shopper's Guide 8th Edition, page B-8. Cybair Limited Publishing, 2001. {{ISBN|0-9680628-1-4}} 2. ^1 {{cite web|url = http://www.beaujonaircraft.com/|title = Beaujon Ultralights|accessdate = 2009-08-02|last = Beaujon|first = Herbert|authorlink = |year = n.d.}} External links
1 : United States ultralight aircraft 1980–1989 |
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