|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||244/203 ; 244/209 ; 244/214 ; 244/215 ; 244/219|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 41 인용 특허 : 0|
The optimum wing flow is thereby maintained more exactly. For transonic wings, the position and strength of compression shocks is also effectively controlled, which leads to a reduction of the direct shock induced separation.
[ We claim:] [1.] In an aircraft having at least one airfoil including a leading edge flap arranged at a leading edge of said airfoil, a high lift flap arranged at a trailing edge of said airfoil, a spoiler, an aileron, and driveable actuators respectively connected to said leading edge flap and said high lift flap, an apparatus for automatically optimizing the aerodynamic effect of said airfoil comprising a process computer with at least one memory area for storing actual flight data and parametric wing data, a plurality of pressure sensors arranged dis...