In order to reduce noise, the invention proposes an airfoil profile (30) for an aircraft (10), such as an unmanned aerial system (11). The airfoil profile (30) comprises a leading edge portion (31) and a trailing edge portion (32) that are spaced apart along a chordwise direction, an airfoil centroid (33); and an upper airfoil surface (40) and a lower airfoil surface (50). The airfoil surfaces (40, 50) are shaped such that the pressure center (Cp) of the lifting force is arranged at the same chord location as the airfoil centroid (33) or closer to the trailing edge portion (32) along the chordwise direction than the airfoil centroid (33). With this, a pitchdown momentum is generated that urges the leading edge portion (31) towards a lower angle of attack (AoA).
AN AIRFOIL PROFILE FOR AN AIRCRAFT AND AERODYNAMIC SURFACES USING SAID AIRFOIL PROFILE
TRAGFLÄCHENPROFIL FÜR EIN FLUGZEUG UND AERODYNAMISCHE OBERFLÄCHEN MIT BESAGTEM TRAGFLÄCHENPROFIL
PROFIL AÉRODYNAMIQUE POUR AÉRONEF ET SURFACES AÉRODYNAMIQUES UTILISANT LEDIT PROFIL AÉRODYNAMIQUE
2024-04-24
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge |
AIRFOIL PROFILE FOR AN AIRCRAFT AND AERODYNAMIC SURFACES USING SAID AIRFOIL PROFILE
Europäisches Patentamt | 2024
|Airfoil profile for aircraft and aerodynamic surface using said airfoil profile
Europäisches Patentamt | 2024
|NTIS | 1975
|