LAK 17

Design and development

The LAK-17 is designed to meet the requirements of the utility category of JAR-22. It is a single-seat mid-wing sailplane of composite construction with a T-tail and flaps, it has a retractable single-wheel main landing gear and has airbrakes on the upper wing surface. The airfoil is a combination of the LAP92-130/15, at its roots, and the LAP-92-150/15, at its tips. The LAK-17 holds water ballast in tanks in the wing and fin. The LAK-17A was certified in November 1994 by the Lithuanian Civil Aviation Authority. A new variant with an improved wing was designated the LAK-17B. All variants have a 15.00 m (49.21 ft) wingspan but a wing with span increased to 18.00 m (59.06 ft) is available as an option; powered self-sustaining versions are also produced.

An optional front electric sustainer engine variant was developed for the LAK-17 by Slovenian engineers at LZ Design. It originally had a 0.9 metre propeller, and the latest versions have a 1.0 metre propeller in the nose driven by an electric motor.

Variants

LAK-17A

Production flapped 15- or 18-metre wingspan sailplane.

LAK-17AT

Powered self-sustaining sailplane variant of the LAK-17A with a Solo 2350 two-cylinder air-cooled two-stroke retractable engine.

LAK-17A FES

A LAK-17A with a front electric sustainer.

LAK-17B

Improved variant with new wing profile and modified geometry.

LAK-17BT

Powered self-sustaining sailplane variant of the LAK-17B with a Solo 2350 retractable engine.

LAK-17B FES

A LAK-17B with a front electric sustainer.

Specifications (LAK-17A with 15 metre wingspan)

Data from

General characteristics

Crew: one

Capacity: 188 kg (414 lb) water ballast

Length: 6.53 m (21 ft 5 in)

Wingspan: 15.00 m (49 ft 2 in)

Height: 1.29 m (4 ft 3 in)

Wing area: 9.06 m² (97 ft²)

Aspect ratio: 24.63

Empty weight: 245 kg (540 lb)

Gross weight: 500 kg (1102 lb)

Performance

Maximum speed: 275 km/h (171 mph)

Maximum glide ratio: 45

Rate of sink: 0.53 m/s (104 ft/min)