The possibility of airfoil drag reduction by active laminar flow control is well known. The reduced airfoil drag compared to conventional laminar flow airfoils can improve the performance of a glider significantly. A dedicated airfoil designed to operate with boundary layer control could be used on a very high performance glider if a structurally sound design can be created and manufactured. This paper deals with the structural design, production and subsequent testing of a 1 m long wing test specimen, containing a spanwise orientated suction slit. The novel feature of this design is a composite truss web for the rear spar with very small individual members. This design permits an undisturbed internal flow of the sucked away air mass. The specimen is designed to meet stiffness and strength requirements approximately equivalent to the ASW 25 glider at the 1/4 semispan position. The test wing box was loaded, and met the torsional stiffness and strength requirements.
Structural solution for a composite glider wing with suction boundary layer control for 100 % laminar flow
Eine strukturierte Lösung für einen Segelflugzeugflügel mit einer Sauggrenzflächenschicht mit 100 % laminarer Strömung
Composites, Part A: Applied Science and Manufacturing ; 28A , 12 ; 1013-1018
1997
6 Seiten, 8 Bilder, 8 Quellen
Aufsatz (Zeitschrift)
Englisch
Boundary-Layer Suction System Design for Laminar-Flying-Wing Aircraft
Online Contents | 2011
|Engineering Index Backfile | 1953
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