Reduction de la Trainee des Avions de Transport par Laminarite Etendue (Aircraft Drag Reduction by Application of Laminar Flow Technology)
Reduction de la Trainee des Avions de Transport par Laminarite Etendue (Aircraft Drag Reduction by Application of Laminar Flow Technology)
- New search for: J. Reneaux
- New search for: J. Reneaux
Drag reduction can be obtained according to the Mach number, the Reynolds number and the wing sweep by the natural laminar flow or laminar flow control concepts. The first is to design airfoils to obtain favorable pressure gradients that have stabilizing effects on laminar boundary layers. The alternative concept is to associate a wall suction of the boundary layer to the previous airfoils. After a survey of the different transition criteria used, several designs of laminar flow wings at O.N.E.R.A. are presented. The natural laminar flow concept has been applied to the design and the test of a horizontal stabilizer for executive aircraft and to the wing design of a short haul aircraft. The laminar flow control activities have been developed with the design of an airfoil for a large long range aircraft and the studies of a fin for the same aircraft.
Document information
Reduction de la Trainee des Avions de Transport par Laminarite Etendue (Aircraft Drag Reduction by Application of Laminar Flow Technology)
1987
40 pages
Report
No indication
English
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