LET L-23 Super Blaník

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L-23 Super Blaník
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Role Two-seat sailplane
National origin Czechoslovakia
Manufacturer Let Kunovice
First flight 1988
Developed from LET L-13 Blanik
Variants Let L-33 Solo

The LET L-23 Super Blaník is a two-seat glider of all-metal structure. The aircraft is primarily used for flight training.

Design and development

The Super Blaník is an improved version of the original LET L-13 Blanik, and is somewhat roomier in front. Differences include a swept fin and a T-tail. To save weight, the new wings were made without flaps, which were rarely used. While flaps were eliminated, airbrakes are still included on the L-23. The airbrakes open on both the top and the bottom of each wing. LET also moved the tailplane to the top of the vertical stabilizer for better protection in case of outlanding. It has a new instrument suite and a new two-piece canopy (with different framing from that on the original L-13) to improve vision.

The aircraft has a two-piece canopy, where the front part opens to the right, and the rear part opens upwards and to the rear. From serial No. 968401 it was delivered with a one-piece canopy, that opens to the right only (with a very small canopy section opening to the rear at the wing root). The maximum number of occupants is two. If the sailplane is to be flown solo, the pilot must be sitting in the front seat and his weight (including parachute and ballast) must be at least 70 kg (154 lb). If the pilot's weight is less than 70 kg (154 lb), it is necessary to use ballast to bring the total weight in the front to at least 70 kg (154 lb). A weighted cushion weighing 15 kg (33 lb) is available to replace the soft seat cushion bottom in the front seat. Additional ballast may need to be added to bring the total to at least 70 kg (154 lb).

The United States Air Force Auxiliary Civil Air Patrol uses the L-23 as a trainer for cadets.

Blanik Aircraft CZ s.r.o. plans a new version of the L-23, the L23NG (New Generation), with winglets, improved fuselage and single canopy with slightly higher performance (L/D ratio: 31).[1]

Specifications

Data from Jane's All The World's Aircraft 1988–89[2]

General characteristics

  • Crew: 2
  • Length: 8.5 m (27 ft 11 in)
  • Wingspan: 16.2 m (53 ft 2 in)
  • Height: 1.9 m (6 ft 3 in)
  • Wing area: 19.15 m2 (206.1 sq ft)
  • Airfoil: root: NACA 632A-615 ; tip:NACA 632A-612
  • Empty weight: 310 kg (683 lb)
  • Max takeoff weight: 510 kg (1,124 lb) dual

Performance

  • Stall speed: 56 km/h (35 mph; 30 kn) at max t/o weight dual
  • Never exceed speed: 256 km/h; 159 mph (138 kn) in smooth air at max t/o weight dual
160 km/h (86 kn; 99 mph) in rough air
150 km/h (81 kn; 93 mph) on aero-tow
120 km/h (65 kn; 75 mph) on winch launch
130 km/h (70 kn; 81 mph) flaps extended
  • g limits: +5.3 -1.5 at max t/o weight dual, +6 -3 at max t/o weight solo
  • Maximum glide ratio: 28 at 90 km/h (49 kn; 56 mph) at max t/o weight dual
  • Rate of sink: 0.82 m/s (161 ft/min) at 80 km/h (43 kn; 50 mph) at max t/o weight dual
  • Wing loading: 26.63 kg/m2 (5.45 lb/sq ft) max dual

See also

Related development
Related lists

References

  1. ↑ L-23 New Generation
  2. ↑ Lua error in package.lua at line 80: module 'strict' not found.

External links

Media related to Lua error in package.lua at line 80: module 'strict' not found. at Wikimedia Commons

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