Patent ID: 8565942

Claim:
A method for determining the ground effect release speed of an aircraft (AC) provided with at least one piloting stick ( 14 ), a main landing gear ( 11 ), ailerons ( 6 G, 6 D) and depth moving aerodynamic surfaces ( 7 , 9 G, 9 D), wherein, during take-off, while said aircraft (AC) is rolling down on a take-off runway (RW), accelerating with said main landing gear ( 11 ) compressed by the mass of said aircraft and by the ground effect and with said ailerons ( 6 G, 6 D) having a partly deflected position (α D ) downwards for maximising the fineness ratio of said aircraft, said method comprising: tilting said piloting stick ( 14 ) in the nose-up direction, to deflect said depth aerodynamic surfaces ( 7 , 9 G, 9 D) upwards for giving said aircraft the attitude (θ TS ) for which the tail ( 13 ) thereof is brought to strike said take-off runway (RW); continuing acceleration of the aircraft, in the tail strike attitude position (θ TS ), until full ballasting-up of said main landing gear ( 11 ); noting the speed of said aircraft upon said ballasting-up, wherein such speed is the desired ground effect release speed; and after said deflection upwards of depth aerodynamic surfaces ( 7 , 9 G, 9 D) for giving said aircraft the tail strike attitude (θ Ts ) and while said main landing gear ( 11 ) is still compressed, deflecting said ailerons ( 6 G, 6 D) fully downwards (α M ), symmetrically, from their partly deflected position (α D ) downwards.