G102 Astir
Astir CS in flight
Role	Standard-class sailplane
National origin	Germany
Manufacturer	Grob Aerospace
Designed by	Burkhart Grob
First flight	December 1974
Number built	1241

The G-102 Astir is a single seat glassfibre Standard Class sailplane, designed by Burkhart Grob and built by Grob. It was the first Grob-designed sailplane, with the first flight in December 1974. (Grob had previously built the Schempp-Hirth Standard Cirrus under licence.)

The Astir CS [Club Standard] is of composite (fiberglass/resin) construction, has a large wing area, a T-tail and water ballast tanks in its wings. The large wing area gives good low speed handling characteristics but rather poor high speed performance compared to other Standard class gliders. In early versions some of the fuselage frame was wood, but this was replaced with a light alloy casting which sometimes cracks after heavy landings. The tail dolly is unusual by being plugged into a vertical hole.

A slightly improved standard-class version, the CS 77, was introduced in 1977. It has a different rudder profile and a slimmer fuselage similar to that of the Speed Astir. The Standard II and Standard III versions followed in the early 1980s, reverting to the higher profile fuselage and with a reduced empty weight and an increased payload. The above specifications are given for the Standard III.

The Astir CS Jeans was similar to the CS 77, but had a fixed main-wheel ahead of its center of gravity, and a tailskid. Its cockpit was fitted in blue denim. Later versions were the Club II and the Club III which also had fixed gear, but the Club III had a tailwheel.

The numbers built of each type were: 536 CS, 244 CS 77, 248 CS Jeans, 61 Club/Standard Astir II and 152 Club/Standard Astir III. A flapped version called the G104 Speed Astir was also produced.

One Astir (now residing at the Steven F. Udvar-Hazy Center), flown by Robert Harris, broke the world absolute altitude record at 49,009 ft (14,938 m) on 17 February 1986. This record lasted until 2006 ^[1].

[edit] Specifications

General characteristics

• Crew: One pilot
• Capacity: 50 kg (110 lb) water ballast
• Wingspan: 15.00 m (49 ft 3 in)
• Wing area: 12.4 m² (133 ft²)
• Aspect ratio: 18.2
• Empty weight: 255 kg (561 lb)
• Gross weight: 450 kg (990 lb)

Performance

• Maximum glide ratio: 38
• Rate of sink: 0.62 m/s (122 ft/min)

[edit] Performance without water ballast

[edit] Best Glide

Glide Ratio of 36 at 50 knots (92 km/h) which gives a sink rate of 141 ft/min (0.71 m/s)
(Can fly 5.9 nm (10.97 km) per 1000 ft)

[edit] Minimum Sink

Glide Ratio of 34 at 41 knots (76 km/h) which gives a sink rate of 122 ft/min (0.62 m/s)
(Can fly 5.6 nm (10.36 km) per 1000 ft)

[edit] At 90 knots (166 km/h)

Glide Ratio of 23 at 90 knots (166 km/h) which gives a sink rate of 393 ft/min (2.00 m/s)
(Can fly 3.8 nm (7.01 km) per 1000 ft)

[edit] Stalling

Stalling: (without airbrakes) 32 knots (60 km/h) (with airbrakes) 35 knots (65 km/h)

[edit] Velocities

Never Exceed: 135 knots (250 km/h)
In Rough Air: 135 knots (250 km/h)
Manoeuvering: 92 knots (170 km/h)
On Aerotow: 92 knots (170 km/h)
On Winch: 64 knots (120 km/h)
Airbrakes: 135 knots (250 km/h)
Gear Down: 135 knots (250 km/h)

[edit] Payloads

Minimum: 70 kg
Maximum: 110 kg

[edit] References

• Sailplane Directory
• Hardy, M. Gliders & Sailplanes of the World. Ian Allan, 1982

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