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Private Aircraft


Two-Seaters

  1. Grob Twin Astir
  2. DG Flugzeugbau DG-500M/22

Single Seaters

  1. DG Flugzeugbau LS8 St
  2. Schleicher ASW-24E
  3. Schempp-Hirth Nimbus 2
  4. DG Flugzeugbau DG-400M/17
  5. Schempp-Hirth Standard Cirrus
  6. Grob Standard Cirrus
  7. Schempp-Hirth Mini Nimbus
  8. Flug un Fahrzeugwerke Diamant
  9. Glasflugel 303 Mosquito
  10. PZL Bielsko SZD 32A Foka 5
  11. Maupin Windrose
  12. Maupin Woodstock
  13. Schneider ES-60 Boomerang
  14. Schneider ES-60 Boomerang II
  15. Schneider ES-60B Super Arrow

 

 

 

Grob Twin Astir

VH-IKM  S/N 3038

Specifications

  • Span:- 17.5m / 57.4ft
  • Length:- 8.1m / 26.6ft
  • Area:- 17.9m2 / 192.7ft2
  • Aspect ratio:- 17.1
  • Airfoil:- Eppler E 603
  • Empty weight:- 420kg / 705lb
  • Payload:- 230 kg / 507 lb
  • Water Ballast:-  90kg / 198lb
  • Gross weight:- 650kg / 1,430lb
  • Wing loading:- 37.79kg/m2 / 7.73lb/ft2
  • Structure:- fibreglass

Performance

  • L/D:- max. 38 @ 110kph / 59kts
  • Min sink:- 0.62m/s / 2.23fps / 1.32kts @ 75kph / 40kts / 46mph
  • Vne:- 250kph / 135kts / 155mph

 

The Twin Astir was a two-seat development of the Standard Class Astir CS. The prototype Twin Astir first flew on 31 December 1976.  VH-IKM is one of the original production aircraft and first flew on 28 December 1977.  Grob's early model Twin Astirs have a retractable landing gear that retracts by folding up to the left and lying horizontally under the rear seat.   Water Ballast tanks are also fitted.  In contrast to later G 103 models, the Twin Astir has the main wheel ahead of the centre of gravity, and does not have a nose wheel. Manufactured with a tailskid, VH-IKM was fitted with a tail wheel in April 1978 upon arrival in Australia. 

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DG Flugzeugbau DG-500M/22

VH-XON S/N 5E64M27

Specifications

  • Span:- 22m / 72.2ft
  • Area:- 18.29m2 / 196.8ft2
  • Aspect ratio:-  19.52
  • Airfoil:- Wortmann FX-73-K-170/20 root; -170/22 tip
  • Empty weight:- 445kg / 981lb
  • Payload:- 305kg / 672lb
  • Water Ballast:- 160kg / 353lb
  • Gross weight:- 750kg / 1,653lb
  • Wing loading:- 41.0kg/m2 / 8.40lb/ft2
  • Structure:-  CFRP/GFRP

Performance

  • L/D:- max 47 @ 111kph / 60kts
  • Min sink:- 0.51m/s / 1.67fps / 0.99kts @ 80kph / 43kts / 50mph
  • Vne:- 270kph / 146kts / 168mph

 

The DG-500 comes in a number of sizes which all share the same basic fuselage. The 500T Elan Trainer, which first flew in 1989 has an unflapped 18 m. wing without provision for Water Ballast; retractable gear is an option. The front cockpit design has been purposely made similar to that of the DG-300 Club. The higher performance versions (DG-50022 Elan and DG-500 M) have a 22 m flapped wing and are, respectively, unpowered and self-launch models. VH-XON is the powered model (DG-500M) and has a liquid cooled Rotax powerplant on an electrically retracting pylon, digital engine instrumentation (DEI) and Water Ballast reduced to 100 kg / 220 lb and comes with a steerable nosewheel. The DEI, which has instrumentation in both cockpits, shows rpm, temperatures, pressures and fuel quantity as well as controlling the amount of fuel injected by the electronic fuel system. Engine retraction is automatic once the propeller has been stopped and centred.  All 22m ships, which have a four piece wing, have retractable gear as standard. Performance of the 500M is similar to the 500/22 Elan, but empty and Gross weights are 565 kg./ 1,246 lb And 825/1,819 lb Respectively. 

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DG Flugzeugbau LS8 T

VH-VPB  S/N 8521

Specifications

  • Span:- 15.0m / 49.2ft or 18.0m / 59.6ft
  • Area:- 10.50m2 / 113ft2  or 11.4m2 / 122.9ft2
  • Aspect ratio:- 21.4 or  28.3
  • Empty weight:- 265 kg / lb / 270 kg / lb
  • Payload:- 260 kg /  573 lb
  • Water Ballast:- 190 kg / 419 lb
  • Gross weight:- 575 kg / 1,267 lb.
  • Wing loading:- 50 kg/m2 / 10.2 lb/ft2 or 50.4 kg/m2 / 10.3 lb/ft2
  • Engine Solo 2350 ca. 18 hp28.4
  • Structure:- GFRP/ CFRP

Performance

  • L/D:- max. 43 or 48
  • Min sink:- 0.59m/s / fps / kts
  • Vne:- 280kph / 151kts / 174mph

 

The LS 8-T is a single seater powered sailplane with carbon fibre wing shell, winglets, T-tail, wing and vertical tail fin water ballast systems, retractable and sprung landing gear, and upper wing surface air brakes.  The LS8-st may be operated in 15m or 18m span and winglets in both versions. The self-sustaining system in the fuselage consists of an extendable aircooled twostroke twin cylinder engine with fixed pitch propeller. This powered sailplane has been produced using the latest technology of industrial fibre design (Glass-, Aramid- and Carbon fibres). It is designed for competition flights high performance combined with excellent handling characteristics.

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Schleicher ASW-24E

VH-XJG  S/N 24826

Specifications

  • Span:- 15.0m / 49.2ft
  • Area:- 10.00m2 / 107.6ft2
  • Aspect ratio:- 22.5
  • Airfoil:- Boermans DU 84-158
  • Empty weight:- 275 kg / 606 lb
  • Payload:- 270 kg / 595 lb
  • Water Ballast:- 170 kg / 375 lb
  • Gross weight:- 500 kg / 1,102 lb.
  • Wing loading:- 50.0 kg/m2 / 10.24lb/ft2
  • Engine 19 kW/ 25 bhp Rotax 275
  • Structure:- GFRP/ CFRP/ Kevlar

Performance

  • L/D:- max. 44 @ 105 kph / 57 kts / 65 mph
  • Min sink:- 0.62m/s / 2.03fps / 1.20kts @ 75kph / 41kts / 47mph
  • Vne:- 280kph / 151kts / 174mph

 

The ASW-24, which first flew in 1987, is the Standard Class successor to the Schleicher ASW-19. Approach control is effected by top surface Schempp-Hirth type airbrakes. Designer Waibel won the 1992 OSTIV Award for significant contributions to safety for the ASW-24 design. The ASW-24E is the self-launching version.

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Last modified: 16 June 2021