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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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Schempp-Hirth Nimbus 2

VH-IZB S/N  43

Specifications

  • Span:- 20.3m / 66.6ft
  • Area:- 14.39m2 / 154.9ft2
  • Aspect ratio:- 28.6
  • Airfoil:- Wortmann FX-67-K-1 70
  • Empty weight:- 355 kg / 782 lb
  • Payload:- 295 kg / 651 lb
  • Gross weight:- (w/water) 650 kg / 1,433 lb
  • Wing loading:- 45.17kg/m2 / 8.25lb/ft2
  • Structure:- fibreglass sandwich

Performance

  • L/D:- max. 49 @ 90 kph / 49 kts / 56 mph
  • Min sink:- 0.49m/s / 1.6fps / 0.95kts @ 76kph / 41kts / 47mph
  • Vne:- 270kph / 146kts / 168mph

 

The Nimbus 2 (developed from the 1969 22 m Nimbus) first flew in 1971. The four piece wing has flaps interconnected with the ailerons with settings which range from +6 to –8 degrees, with 20 degrees for landing. 

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DG Flugzeugbau DG-400M/17

VH-GPH S/N 4-56

Specifications

  • Span:- 17m / 55.8ft
  • Area:- 10.57m2 / 113.8ft2
  • Aspect ratio:-  27.3
  • Airfoil:- Wortmann FX67-K-170-17 root, FX-60-K-126 tip 
  • Empty weight:- 310kg / 683lb
  • Payload:- 155kg / 342lb
  • Gross weight:- 460kg / 1,014lb
  • Wing loading:- 43.52kg/m2 / 8.91lb/ft2
  • Engine:- 32 kW/ 43 bhp Rotax 505
  • Structure:-  CFRP/GFRP

Performance

  • L/D:- max 45 @ 109kph / 59kts
  • Min sink:- 0.50 m/s / 1.64 fps / 0.97 kt  @ 80kph / 43kts / 50mph
  • Vne:- 270kph / 146kts / 168mph

 

The DG-400 uses the wings and most systems of the DG-202. A modified fuselage with a slightly enlarged boom and carbon fibre reinforcements was required for the engine, which is a relatively large unit with electric starter and electric retraction. As typical for the time, the engine extends into the airflow together with the propeller and supporting pylon. This powerful installation, associated with a user-friendly engine control unit - a field where DG Flugzeugbau continues to lead up to this day - ensured that the DG-400 was significantly safer and easier to operate than other self-launching gliders, ensuring its success.  The type was not aimed at competitions, but rather at leisure flying. Nevertheless, several World Gliding Records were achieved in DG-400s. Although superseded by more modern self-launching sailplanes, the DG-400 is still very popular, being one of the favourites in the second-hand market.

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Schempp-Hirth Standard Cirrus

VH-GOX  S/N  120

Specifications

  • Span:- 15.0m / 49.2ft
  • Area:- 10.00m2 / 107.5ft2
  • Aspect ratio:- 22.5
  • Airfoil:- Wortmann FX-S-02-196 mod.
  • Empty weight:- 220 kg / 485 lb
  • Payload:- 170 kg / 375 lb
  • Water Ballast:- 60 kg / 132 lb
  • Gross weight:- 390 kg / 860 lb
  • Wing loading:- 39.0 kg/m2 / 7.99 lb/ft2
  • Structure:- steel-tube centre section framework, fibreglass sandwich fuselage PVC foam core wings with fibreglass skin.

Performance

  • L/D:- max 38 @ 90kph / 49kts / 56mph
  • Min sink:- 0.57m/s / 1.87fps / 1.01kts @ 70kph / 38kts / 44mph
  • Vne:- 220kph / 119kts / 137mph

 

The Standard Cirrus, from Schempp-Hirth Flugzeugbau GmbH, Kirchheim, Germany, was introduced in 1969. It was the creation of Klaus Holighaus, one of the most successful and respected sailplane designers. The Standard Cirrus was a follow-on to the original Open Class Cirrus design but is a completely different aircraft.  It has a 15m wing with airbrakes on the top surface only, an all-moving T-tail, 0.75 degree wing twist, and a steel tube skeleton in the wing-fuselage centre section.  VH-GOX first flew in 1970 and was originally registered in the UK as BGA 1645.

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Grob Standard Cirrus

VH-GOR  S/N  491G

Specifications

  • Span:- 15.0m / 49.2ft
  • Area:- 10.00m2 / 107.5ft2
  • Aspect ratio:- 22.5
  • Airfoil:- Wortmann FX-S-02-196 mod.
  • Empty weight:- 220 kg / 485 lb
  • Payload:- 170 kg / 375 lb
  • Water Ballast:- 60 kg / 132 lb
  • Gross weight:- 390 kg / 860 lb
  • Wing loading:- 39.0 kg/m2 / 7.99 lb/ft2
  • Structure:- steel-tube centre section framework, fibreglass sandwich fuselage PVC foam core wings with fibreglass skin.

Performance

  • L/D:- max 38 @ 90kph / 49kts / 56mph
  • Min sink:- 0.57m/s / 1.87fps / 1.01kts @ 70kph / 38kts / 44mph
  • Vne:- 220kph / 119kts / 137mph

 

The Standard Cirrus was designed by Klaus Holighaus from Schempp-Hirth Flugzeugbau.  176 of this type were built under license by Burkhart Grob GmbH, Mindelheim, Germany from 1972 to 1975 and VH-GOR is one of these.  While similar to VH-GOX above, GOR has 1.5 degree wing twist.

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Schempp-Hirth Mini Nimbus

VH-UIW  S/N  93

Specifications

  • Span:- 15.0m / 49.2ft
  • Area:- 9.86m2 / 107.5ft2
  • Aspect ratio:- 23.0
  • Airfoil:- Wortmann FX-67-K-150
  • Empty weight:- 235 kg / 518 lb
  • Payload:- 215 kg / 474 lb
  • Water Ballast:- 120 kg / 265 lb
  • Gross weight:- 450 kg / 992 lb
  • Wing loading:- 45.6 kg/m2 / 9.34 lb/ft2
  • Structure:- steel-tube centre section framework, fibreglass sandwich fuselage PVC foam core wings with fibreglass skin.

Performance

  • L/D:- max 41 @ 106kph / 57kts
  • Min sink:- 0.57m/s / 1.87fps / 1.01kts @ 78kph / 42kts / 48mph
  • Vne:- 250kph / 135kts / 137mph / 155mph

 

The Mini Nimbus was a development of the Cirrus with the features of the Nimbus 2, having camber changing flaps.  The flaps give five positions between -7 and +10.  The airbrakes open from the upper wing surface, just forward of the flap, and will increase the flap when fully extended. 

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Flug un Fahrzeugwerke Diamant

VH-GVR  S/N 74

Specifications

  • Span:- 18.0m / 59.0ft 
  • Area:- 14.28m2 / 153.7ft2
  • Aspect ratio:- 22.7 
  • Airfoil:- Wortmann FX-62-Z-153
  • Empty weight:- 280kg / 617lb 
  • Payload:- 160 kg / 353 lb
  • Gross weight:- 440 kg / 970 lb 
  • Wing loading:- 30.8 kg/m2 / 6.34 lb/ft2
  • Structure:- foam/ glassfibre sandwich

Performance

  • L/D:- max. 45 @ 100kph / 54kts / 62mph
  • Min sink:- 0.52m/s / 1.71fps / 1.01kts @ 72kph / 39kts / 45mph
  • Vne:- 200kph / 108kts / 124mph

 

The development of this early all-fibreglass sailplane began at the Swiss Federal Institute of Technology in Zurich under the direction of Prof. Rauscher, first flying with a new fuselage and tailplane married to wings from a schleicher Ka-6 (the Ka Bi-Vo). Further development was taken over by Flug un Fahrzeugwerke (FFA) which used flapped 15 m. Hutter H-30TS wings, first flying in 1964. After production 13 examples of this model (the HBV Diamant), production shifted to the Diamant 16.5 with a new 16.5 m. wing designed and built by FFA. This was the first all glass fibre production sailplane, not using balsa or other wood sandwiched between the fibreglass layers. The Diamant 18 is an 18 m. development of the 16.5, first flying in 1968, with extended inboard wing and flap sections and a new wingtip cap. 

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Glasflugel 303 Mosquito

VH-FQR  S/N 138

Specifications

  • Span:- 15.0m / 49.2ft
  • Area:- 9.86m2 / 106.1ft2
  • Aspect ratio:- 23
  • Airfoil:- Wortmann FX-67-K-150
  • Empty weight:- 227kg / 500lb
  • Payload:- 193kg / 426lb
  • Water Ballast:- 120kg / 265lb
  • Gross weight:- 420kg / 926lb
  • Wing loading:- 42.6 kg/m2 / 8.72 lb/ft2
  • Structure:- fibreglass 

Performance

  • L/D:- max. 42 @ 114kph / 62kts
  • Min sink:- 0.58m/s / 1.9fps / 1.08kts @ 80kph / 43kts / 50mph
  • Vne:- 250kph / 135kts / 155mph

 

The mosquito was derived from the Club Libelle and first flew in February 1976.  The airbrake/flap combination comprises trailing edge flaps and rear-edge rotating brake flaps.  The flap lever operates the flaps and droops the ailerons, with a second lever operating the brake flap on the upper surface of the wing.  It has a retractable undercarriage and forward opening canopy.

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PZL Bielsko SZD 32A Foka 5

VH-GZD  S/N W-481

Specifications

  • Span:- 15.0m / 49.2ft
  • Area:- 12.2m2 / 131ft2
  • Aspect ratio:- 19.4
  • Airfoil:- NACA 63(3)-618
  • Empty weight:- 257kg / 567lb
  • Payload:- 128kg / 282lb
  • Gross weight:- 385kg / 849lb
  • Wing loading:- 31.6kg/m2 / 6.48lb/ft2
  • Structure:- wood, ply/ plastic sandwich skins 

Performance

  • L/D:- max. 34 @ 87kph / 47kts / 54mph
  • Min sink:- 0.67m/s / 2.2fps / 1.30kts @  78kph / 42kts / 48mph
  • Vne:- 260kph / 140kts / 161mph
The Foka 5 is a Standard Class design, which first flew in 1969. It incorporates the handling characteristics of the Foka 4 with a Wortmann profile and higher Aspect ratio wing; 45 degree to 45 degree roll rate is less than three seconds. The ailerons and free-flying horizontal tail are mass balanced. 

Maupin Windrose

VH-UII  S/N GFA-HB-120

Specifications

  • Span:- 12.6m / 41.5ft
  • Area:- 8.92m2 / 96ft2
  • Aspect ratio:- 17.9
  • Empty weight:- 232kg / 512lb
  • Payload:- 103kg / 228lb
  • Gross weight:- 336kg / 740lb
  • Wing loading:- 37.6 kg/m2 / 7.7 lb/ft2
  • Structure:- wood/foam/fabric

Performance

  • L/D:- 21 @ 84 kph / 45 kt / 52 mph
  • Min sink:- 0.70 m/s / 2.3 fps / 1.36 kt
  • Vne - 204 kph / 110 kts / 127 mph

Designed to meet SHA Homebuilt Sailplane Design Contest criteria: easy to built, low cost, soarable, self-launching, safe, the definitive powered Windrose first flew in 1984. The structural backbone is a hollow plywood box with corners longerons which carry the engine mounts, landing gear and fibreglass cockpit shell. The wings are shaped foam covered with fibreglass, but without a conventional spar. The ‘spars’ are bands of unidirectional roving epoxied into recesses in the upper and lower wing skins, and separated by rows of vertical dowels between the bands to take compression loads off the foam. Ailerons are set inboard from the root to approximately two-thirds Span operated by pushrods from the fuselage. The wing Structure is free of controls, pushrods, cables etc. Glidepath control is by a triangular spoiler which rises above the wing centre section. Both tail surfaces are all-moving. 

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Maupin Woodstock

VH-IKL  S/N GFA-HB-123

Specifications

  • Span:- 12.0m / 39.2ft
  • Area:- 9.73m2 / 104.7ft2
  • Aspect ratio:- 14.5
  • Empty weight:- 111kg / 245lb
  • Payload:- 95kg / 210lb
  • Gross weight:- 206kg / 455lb
  • Wing loading:- 21 kg/m2 / 4.3 lb/ft2
  • Structure:- wood 

Performance

  • L/D:- max. 24 
  • Min sink:- 0.79m/s / 2.6fps / 1.54kts
  • Vne - 154 kph / 83 kts / 96 mph

Woodstock was designed with a wing having an 18 % section for the root, 13 % at the tip and no twist. The principal design objectives were low cost and simplicity of construction. Douglas Air was used for all major structural parts and all tail and wing skins were birch. It first flew in 1978 and won the Sailplane Homebuilders Association design contest in 1984. A tail wheel is an option instead of a skid. The main wheel is fixed. Approach control is by wing top surface spoilers. As an option, wings of 13.1 m./ 43.0 ft. were offered for which specifications are given in parenthesis.

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Schneider ES-60 Boomerang

VH-GQO  S/N 82

Specifications

  • Span:- 15.0m / 49.2ft
  • Area:- 12.82m2 / 138ft2
  • Aspect ratio:- 17.5
  • Airfoil:- Wortmann FX-61-184/60-126
  • Empty weight:- 241kg / 531lb
  • Payload:- 106kg / 234lb
  • Gross weight:- 347kg / 765lb
  • Wing loading:- 26.07kg/m2 / 5.5lb/ft2
  • Structure:- all wood. 

Performance

  • L/D:- max. 31 @ 90kph / 49kts / 56mph
  • Min sink:- 0.72m/s / 2.35fps / 1.39kts @ 74kph / 40kts / 46mph
  • Vne:- 225 kph / 121 kts / 139 mph

 

The ES-60 Boomerang was designed at the request of the Gliding Federation of Australia as a fast and strong Standard Class sailplane for competitions.

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Schneider ES-60 Boomerang II

VH-GTH  S/N 98

Specifications

  • Span:- 15.0m / 49.2ft
  • Area:- 12.82m2 / 138ft2
  • Aspect ratio:- 17.5
  • Airfoil:- Wortmann FX-61-184/60-126
  • Empty weight:- 241kg / 531lb
  • Payload:- 106kg / 234lb
  • Gross weight:- 347kg / 765lb
  • Wing loading:- 26.07kg/m2 / 5.5lb/ft2
  • Structure:- all wood. 

Performance

  • L/D:- max. 31 @ 90kph / 49kts / 56mph
  • Min sink:- 0.72m/s / 2.35fps / 1.39kts @ 74kph / 40kts / 46mph
  • Vne:- 225 kph / 121 kts / 139 mph

 

The ES-60 Boomerang was designed at the request of the Gliding Federation of Australia as a fast and strong Standard Class sailplane for competitions. VH-GTH is the Mark II model, retaining the original all-moving tail.

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Schneider ES-60B Super Arrow

VH-GXS  S/N 107

Specifications

  • Span:- 15.0m / 49.2ft
  • Area:- 12.87m2 / 138.6ft2
  • Aspect ratio:- 17.5
  • Airfoil:- Wortmann FX-61-184/60-126
  • Empty weight:- 221kg / 488lb
  • Payload:- 126kg / 277lb
  • Gross weight:- 347kg / 765lb
  • Wing loading:- 29.96kg/m2 / 5.52lb/ft2
  • Structure:- all wood. 

Performance

  • L/D:- max. 31 @ 90kph / 49kts / 56mph
  • Min sink:- 0.7m/s / 2.3fps / 1.39kts @ 74kph / 40kts / 46mph
  • Vne:- 225 kph / 121 kts / 139 mph

 

The Super Arrow is a single-seat standard class glider designed by Harry Schneider and first flew in 1969.  While the aircraft is a development of the ES59 Arrow, the ES60B is identical to the ES60 Boomerang (above) except that the tailplane is conventional with a separate elevator.

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Last modified: 25 July 2008