| LS6-A | |
|---|---|
 LS6A of AAVE at Buno-Bonnevaux (FR) airfield | |
| General information | |
| Type | 15 metre class and 18 metre class sailplane |
| National origin | Germany |
| Manufacturer | Rolladen-Schneider |
| Designer | |
| Number built | 375 |
| History | |
| First flight | 1983 |
The Rolladen-Schneider LS6 is a 15 metre and 18 metre single-seat flapped glider manufactured by Rolladen-Schneider Flugzeugbau GmbH between 1984 and 2003.
The prototype of the LS6, successor to the LS3 in the FAI 15 metre Class, made its first flight in 1983. Having entered production one year later, the LS6 had an uncommonly long production run ended by Rolladen-Schneider's entry into receivership in 2003. A total of 375 of all versions were built.
A watershed design, the LS6 introduced carbon reinforced plastic as a structural material in LS-gliders, thin profiles for wings and empennage, wing extensions and other features that have been retained in all subsequent types developed by the company. The Akaflieg Darmstadt D41, the LS9 and the Akaflieg Köln LS11 all have wings built in the LS6 moulds.
Bettering the record of the LS4 in the Standard Class, the LS6 dominated the 15 metre Class over nearly a decade, winning the first two places at the 1985 World Gliding Championships at Rieti in Italy, the first three places at the 1987 Worlds at Benalla in Australia, the first four places in the 1991 World Championships at Uvalde in the United States and the first two places in the 1993 World Championships at Borlänge in Sweden.
The type consolidated Rolladen-Schneider's reputation for well rounded, easy to fly gliders that do well in any conditions, being known for its superb handling, tolerance of piloting technique and environment (turbulence, rain, contamination by insects) as well as for good glide ratios over a wide speed range.
The LS6 is succeeded by the LS10, to be produced by DG Flugzeugbau GmbH.
The designer Wolf Lemke decided to retain the wing area of the LS3 but with a double trapezoid wing plan approaching the ideal elliptical shape. A new profile with higher speed potential was selected, the FX 81-K-130 developed in 1981 by University of Stuttgart aerodynamicist Professor Franz Wortmann. Albeit having a thickness-to-chord ratio of only 13%, this conservative profile has a remarkably benign behaviour that pays handsomely in terms of ease of handling and tolerance to environmental conditions. A slightly thicker version of this profile was developed with Prof. Wortmann for the outer wing, assuring healthy stall characteristics without requiring any washout. Profiles of the same family were selected for the slender, wide-span horizontal stabiliser.
A new fuselage, shorter and slimmer than that of the LS3 and LS4, was developed for the LS6. This fuselage and its horizontal stabiliser have been used, with minor modification, for all subsequent LS designs up to the LS10.
The slender wings required the use of a carbon reinforced main spar for structural feasibility. The horizontal stabiliser is a spareless carbon sandwich shell. The full-span flaperons are divided into six segments and built as aramid / foam sandwiches allowing a very light and rigid construction. Fairings on the upper wing surface accommodate the tall flaperon bellcranks. The elevator is a carbon / aramid shell except for the LS6-a that employed an Aramid / corrugated paper construction. The fuselage is built as a single shell of glass-reinforced plastic, except in the area of the cockpit that is a double shell for passive safety. A safety cockpit was developed for the -c variant with additional glass, carbon and aramid reinforcements, following crash tests carried out in-house by Wolf Lemke anticipating later TÜV Rheinland crashworthiness recommendations.
The wing-flaperon gaps were originally sealed by internal Teflon S seals on the top side and by thin metal strip seals sliding over Teflon on the bottom side. PET film seals later became standard on both surfaces. The original water ballast system had four interconnected and unvented ballast bags with a total capacity of 140 litres, with a central valve and a single dumping orifice under the fuselage.
Data fromJane's All the World's Aircraft 1988-89 [1]
General characteristics
Performance
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