A method of providing an aircraft having a fuselage, and a wing configured for extensive laminar flow at design cruise conditions, comprising providing wing biconvex-type airfoils having a ratio t/c of maximum airfoil thickness, t, to chord, c, at each span location, such that the average of said ratio along the wing span, outboard of a zone of fuselage influence, is not more than approximately 0.024 times the square root of the supersonic design cruise Mach number M, and wherein for values of M between 1.3 and 2.8, the corresponding maximum values of said average of said ratio t/c are approximately linearly proportional to maximum values between 0.027 and 0.040.
LAMINAR FLOW WING OPTIMIZED FOR SUPERSONIC AND HIGH SUBSONIC CRUISE AIRCRAFT
AILE A ECOULEMENT LAMINAIRE OPTIMISEE POUR AERONEF A VITESSE DE CROISIERE SUPERSONIQUE ET SUBSONIQUE
2015-04-07
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |
LAMINAR FLOW WING OPTIMIZED FOR SUPERSONIC AND HIGH SUBSONIC CRUISE AIRCRAFT
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