An airfoil portion includes an outer skin member and an inner stiffening member. Either the outer skin member or the inner stiffening member or both are arranged to delimit a chamber. The chamber is configured to contain an inner pressure, wherein the inner pressure differs from a pressure external to the chamber. In an embodiment, an aircraft includes such an airfoil portion. A method for providing such an airfoil portion with a chamber is also described.
Airfoil portion with a chamber
2018-05-08
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge |
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