SZD-45 Ogar

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The SZD-45 Ogar (Greyhound) is a T-tailed cantilever high wing monoplane of wooden, aluminium and fibreglass construction designed and manufactured in Poland.

Design and development

Designed bu Dipl.-Ing. Tadeusz Labuc, the 2-seat Ogar is intended for training glider pilots from ab-initio to advanced stages as well as cross-country flying. The first prototype,(reg. no. SP-0001), first flew on 29 May 1973 powered by a 34 kW (45 hp) Stark-Stamo engine. Due to the Stamo engine being unavailable, production SZD-45A Ogars were built with 51 kW (68 hp) Limbach SL1700EC engines and later with Franklin 2A-120 engines as the SZD-45-2 Ogar F.[1]

Of pod and boom layout the Ogar has a T-tail on a tubular Aluminium alloy tubular boom extending from the keel of the fuselage pod, which houses the cockpit and engine. A variety of materials are used in construction, with a glass-fibre cockpit shell over two load bearing wooden frames. The wings are of wooden single spar construction skinned with plywood and covered with glass-fibre. The engine is mounted at the rear of the fuselage pod, aft of the wing trailing edge at the same level and driving a pusher propeller. The undercarriage consists of a semi-retractable mainwheel fitted with a disc brake, steerable tailwheel and optional outrigger wheels on flexible struts at the wing-tips. Accommodation for two pilots is provided side-by-side under an aft-hinged upward opening canopy. The Ogar was certified for simple aerobatics.[1]

Of the 64 production aircraft 41 were exported;those destined for the United States were powered by dual ignition, turbocharged, Revmaster/Volkswagen VW 2962 engines.[1]

Variants

SZD-45 Ogar
The prototype powered by a 34 kW (45 hp) Stark-Stamo engine.[1]
SZD-45A Ogar
Initial production variant powered by a 51 kW (68 hp) Limbach SL1700EC engines.[1]
SZD-45-2 Ogar F
Later production aircraft powered bya 45 kW (60 hp) Franklin 2A-120A (later 2A-120CP) 2-cyl air-cooled horizontally opposed pston engine.[1]

Specifications (SZD-45A Ogar)

Data from Jane's World Sailplanes and Motor Gliders,[1] Gliders & Sailplanes of the World[2]

General characteristics

  • Crew: 2
  • Length: 7.95 m (26 ft 1 in)
  • Wingspan: 17.53 m (57 ft 6 in)
  • Height: 1.72 m (5 ft 8 in)
  • Wing area: 19.1 m2 (206 sq ft)
  • Aspect ratio: 16.2
  • Airfoil: Wortmann FX-61-168/1261
  • Empty weight: 470 kg (1,036 lb)
  • Max takeoff weight: 700 kg (1,543 lb)
  • Fuel capacity: 22 kg (48.5 lb)
  • Powerplant: 1 × Limbach SL 1700EC 4-cyl. air-cooled horizontally opposed piston engine, 50.7 kW (68.0 hp)
  • Propellers: 2-bladed Hoffmann pusher propeller

Performance

  • Maximum speed: 180 km/h (112 mph; 97 kn) at sea level in straight and level flight
  • Stall speed: 68 km/h (42 mph; 37 kn)
  • Max Rough air speed: 89 km/h (55 mph; 48 kn)
  • Never exceed speed: 225 km/h (140 mph; 121 kn)
  • Range: 549 km; 296 nmi (341 mi)
  • Maximum glide ratio: 27.5 at 100 km/h (62 mph; 54 kn)
  • Rate of sink: 0.96 m/s (189 ft/min) at 73 km/h (45 mph; 39 kn)
  • Wing loading: 36.6 kg/m2 (7.5 lb/sq ft)


Notes

  1. ↑ 1.0 1.1 1.2 1.3 1.4 1.5 1.6 1.7 1.8 1.9 Coates, Andrew (1980). Jane's World Sailplanes and Motor Gliders. London: Jane's Publishing Company. p. 133. ISBN 0 7106 0017 8. 
  2. ↑ Hardy, Michael (1982). Gliders & Sailplanes of the World. Shepperton: Ian Allan Ltd. p. 173. ISBN 0 7110 1152 4. 

References

  • Hardy, Michael (1982). Gliders & Sailplanes of the World. Shepperton: Ian Allan Ltd. p. 173. ISBN 0 7110 1152 4. 
  • Coates, Andrew (1980). Jane's World Sailplanes and Motor Gliders. London: Jane's Publishing Company. p. 133. ISBN 0 7106 0017 8. 

External links

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