Wassmer WA-30 Bijave

From Wikipedia, the free encyclopedia
Jump to navigation Jump to search
WA-30 Bijave
Bijave Sinj.jpg
Role Two-seat training glider
National origin France
Manufacturer Wassmer Aviation
First flight 17 December 1958
Number built 285+
Developed from Wassmer WA-21 Javelot

The Wassmer WA-30 Bijave is a French two-seat advanced training glider designed and built by Wassmer Aviation of Issoire.[1]

Design and development[edit]

The WA-30 Bijave is two-seat development of the Wassmer WA-21 Javelot II and the first Bijave flew on 17 December 1958 from Issoire Aerodrome.[1] The Bijave is a cantilever shoulder-wing monoplane with a welded steel tube fuselage covered with fabric and reinforced plastic.[1] The wing is made from wood, covered in birch forward of the spar and fabric to the rear, it has no flaps but is fitted with retractable perforated wooden airbrakes.[1] The pilot and passenger sit in tandem in an enclosed cockpit with individual transparent canopies.[1] The landing gear is a retractable monowheel, a wooden rubber-sprung skid under the nose and a steel tailskid.[1]

WA30 Bijave
Wassmer 30 Bijave with factory decoration
WA30 Bijave
Wassmer 30 Bijave landing

Specifications[edit]

Data from Jane's All the World's Aircraft 1973-74[1] The World's Sailplanes:Die Segelflugzeuge der Welt:Les Planeurs du Monde Volume II[2]

General characteristics

  • Crew: 2
  • Length: 9 m (29 ft 6 in)
  • Wingspan: 16.85 m (55 ft 3 in)
  • Height: 2.74 m (9 ft 0 in)
  • Wing area: 19.2 m2 (207 sq ft)
  • Aspect ratio: 15
  • Airfoil: Root: NACA 63821, Tip: NACA 63415
  • Empty weight: 295 kg (650 lb)
  • Gross weight: 500 kg (1,102 lb)

Performance

  • Stall speed: 60 km/h (37 mph; 32 kn)
  • Never exceed speed: 200 km/h (124 mph; 108 kn)
  • Rough air speed max: 150 km/h (93.2 mph; 81.0 kn)
  • Aerotow speed: 130 km/h (80.8 mph; 70.2 kn)
  • Winch launch speed: 100 km/h (62.1 mph; 54.0 kn)
  • Terminal velocity: with full airbrakes 190 km/h (118 mph; 103 kn)
  • g limits: +5.33 -2.13 at 220 km/h (136.7 mph; 118.8 kn)
  • Maximum glide ratio: 27 at 85 km/h (52.8 mph; 45.9 kn)
  • Rate of sink: 0.75 m/s (148 ft/min) at 78 km/h (48.5 mph; 42.1 kn)
  • Wing loading: 26 kg/m2 (5.3 lb/sq ft)

See also[edit]

Related lists

References[edit]

Notes
  1. ^ a b c d e f g Taylor, ed. (1973). Jane's All the World's Aircraft 1973-74. London, United Kingdom: Jane's Yearbooks. ISBN 0-354-00117-5. |first1= missing |last1= in Authors list (help)
  2. ^ Shenstone, B.S.; K.G. Wilkinson (1963). The World's Sailplanes:Die Segelflugzeuge der Welt:Les Planeurs du Monde Volume II (in English, French, and German) (1st ed.). Zurich: Organisation Scientifique et Technique Internationale du Vol a Voile (OSTIV) and Schweizer Aero-Revue. pp. 88–89.
Bibliography
  • Shenstone, B.S.; K.G. Wilkinson (1963). The World's Sailplanes:Die Segelflugzeuge der Welt:Les Planeurs du Monde Volume II (in English, French, and German) (1st ed.). Zurich: Organisation Scientifique et Technique Internationale du Vol a Voile (OSTIV) and Schweizer Aero-Revue. pp. 88–89.
  • Taylor, ed. (1973). Jane's All the World's Aircraft 1973-74. London, United Kingdom: Jane's Yearbooks. ISBN 0-354-00117-5. |first1= missing |last1= in Authors list (help)