Asymmetric aerofoil profile with defined curvatures - has max. thickness above and below chord at specified distances from leading edge

The aerofoil profile (1) has the outside (2) and inside (3) asymmetrical relative to the reference abscissa (OX) coinciding with the chord (4) and leading (O) and trailing (5) edges. The boundaries (2, 3) each have a first variable-curvature convex portion (6, 7) up to their maximum distance (Y1 Y2) from the chord (at A and F) to accelerate fluid flow and reduce its pressure, and a second portion (8, 10 and 9, 11) subdivided into a first convex part of variable moderate curvature (8, 9, from A and F), and a second part with zero or near-zero curvature (10, 11). The second part is 50-96% of the chord length (1) and the distances (Y1, Y2) are at a length (X1, X2) from the leading edge at least 22% of the chord length (1) whilst the ratio Y2/Y1 is between 0.25-1. PROFIL AERODYNAMIQUE A HAUTES PERFORMANCES POUR VOILURE D'AERONEF.SELON L'INVENTION, CE PROFIL EST BICONVEXE ET TEL QUE LA VOILURE CORRESPONDANTE COMPORTE UN MAITRE-COUPLE AVANCE ET UNE COURBURE AU MOINS SENSIBLEMENT NULLE SUR LA MAJEURE PARTIE DES SURFACES PORTANTES D'EXTRADOS ET D'INTRADOS, EN AVAL DUDIT MAITRE-COUPLE, LE POINT D'EPAISSEUR MAXIMAL DE L'INTRADOS ETANT PLUS PROCHE DU BORD D'ATTACHE QUE LE POINT D'EPAISSEUR MAXIMAL DE L'EXTRADOS.REALISATION DE VOILURES FIXES OU TOURNANTES D'AERONEF.