초록 ▼

A two element aerofoil, and wing element based thereon, is provided, including a primary aerofoil element including a leading edge of the aerofoil and a secondary aerofoil element including a trailing edge of the aerofoil. A gap is provided between the primary aerofoil element and the secondary aero

A two element aerofoil, and wing element based thereon, is provided, including a primary aerofoil element including a leading edge of the aerofoil and a secondary aerofoil element including a trailing edge of the aerofoil. A gap is provided between the primary aerofoil element and the secondary aerofoil element. The primary aerofoil element has at least one of a profile, orientation and location with respect to a respective at least one of a profile, orientation and location of the secondary aerofoil element that is configured for minimizing or avoiding accretion of contaminant on the secondary aerofoil element when subjected to an airflow that includes the contaminant, at least at one design set of conditions. A method for designing a two element aerofoil is also provided.

대표청구항 ▼

1. A two element aerofoil comprising a primary aerofoil element including a leading edge of the aerofoil and a secondary aerofoil element including a trailing edge of the aerofoil, and comprising a gap between said primary aerofoil element and said secondary aerofoil element, the primary aerofoil el

1. A two element aerofoil comprising a primary aerofoil element including a leading edge of the aerofoil and a secondary aerofoil element including a trailing edge of the aerofoil, and comprising a gap between said primary aerofoil element and said secondary aerofoil element, the primary aerofoil element having at least one of a profile, orientation and location with respect to a respective at least one of a profile, orientation and location of said secondary aerofoil element configured for minimizing or avoiding accretion of contaminant on said secondary aerofoil element when subjected to an airflow comprising the contaminant, at least at one design set of conditions, wherein the contaminant is in the form of particulate matter flowing in a downstream direction with respect to said leading edge of said aerofoil, andwherein said aerofoil comprises a profile configured to ensure that at least some streamlines proximate to said pressure surface of said primary aerofoil element follow a path including over a suction surface of said secondary aerofoil element via said gap, while concurrently providing a trajectory to particulate matter flowing in said at least some streamlines proximate to said pressure surface of said primary aerofoil element to cause said particulate matter to overshoot said gap. 2. The aerofoil according to claim 1, wherein a pressure surface of said primary aerofoil element comprises a pressure surface profile configured for minimizing accretion of said particulate matter on said secondary aerofoil element. 3. The aerofoil according to claim 1, wherein said pressure surface profile is configured for minimizing flow into said gap of said particulate matter that may be flowing over said pressure surface. 4. The aerofoil according to claim 3, wherein said pressure surface profile is configured for minimizing or preventing flow into said gap of said particulate matter that may be flowing along or proximate to a boundary layer over said pressure surface. 5. The aerofoil according to claim 1, wherein said pressure surface profile is further configured to enable airflow through said gap for enabling aerodynamic operation of said two element aerofoil. 6. The aerofoil according to claim 5, wherein said airflow through said gap is generally consistent with providing high lift aerodynamic characteristics to said aerofoil. 7. The aerofoil according to claim 1, wherein said particulate matter comprises at least one of ice, snow, rain, water droplets, sand, smoke particles and dust particles. 8. The aerofoil according to claim 1, wherein said pressure surface profile comprises a convex curvature along a portion of the chord of said primary aerofoil element, said portion being intermediate between said leading edge of the aerofoil and a trailing end of said primary aerofoil element. 9. The aerofoil according to claim 1, wherein said pressure surface profile comprises a concave portion configured for imparting a centrifugal force component to said particulate matter, and a downstream convex portion joined thereto at an inflexion point. 10. The aerofoil according to claim 1, wherein said primary element comprises a first cross-sectional thickness that effectively overlaps a second cross-sectional thickness of the secondary element when viewed from the flow direction upstream of the aerofoil. 11. The aerofoil according to claim 1, wherein said primary element comprises a first cross-sectional thickness having a boundary corresponding to the pressure side of the primary element that effectively overlaps at least an upstream portion of the pressure surface of the secondary element when viewed from the flow direction upstream of the aerofoil. 12. The aerofoil according to claim 11, wherein said secondary element comprises a deflection in the range between about +25 degree and about −25 degrees. 13. The aerofoil according to claim 1, wherein said aerofoil is configured as a high lift two element aerofoil. 14. The aerofoil according to claim 1, wherein a leading edge of said primary aerofoil element is blunt having a first leading edge radius, wherein a ratio of said first radius to a chord of said aerofoil is greater than a threshold value, said threshold value representing a minimum radius to chord ratio obtained from geometric data of NACA 4-digit aerofoils that have a value of thickness to chord ratio that is comparable to a thickness to chord ratio of said aerofoil. 15. The aerofoil according to claim 1, wherein a leading edge of said secondary aerofoil element is blunt having a second leading edge radius, wherein a ratio of said second radius to a chord of said second element is greater than a threshold value, said threshold value representing a minimum radius to chord ratio obtained from geometric data of NACA 4-digit aerofoils that have a value of thickness to chord ratio that is comparable to a thickness to chord ratio of said second element. 16. A wing wherein at least a span portion thereof comprises wing sections corresponding to at least one aerofoil of claim 1. 17. An air vehicle comprising at least one wing according to claim 16. 18. An air vehicle according to claim 17, wherein said air vehicle is a UAV. 19. A method for minimizing or avoiding accretion of contaminant on a two element aerofoil, said aerofoil comprising a primary aerofoil element including a leading edge of the aerofoil and a secondary aerofoil element including a trailing edge of the aerofoil, and a gap therebetween, the method comprising providing the primary aerofoil element with at least one of a profile, orientation and location with respect to a respective at least one of a profile, orientation and location of said secondary aerofoil element such as to minimize or avoid accretion of contaminant on said secondary aerofoil element when subjected to an airflow comprising said contaminant, at least at one design set of conditions, wherein the contaminant is in the form of particulate matter flowing in a downstream direction with respect to said leading edge of said aerofoil, andwherein said aerofoil is provided with a profile configured to ensure that at least some streamlines proximate to said pressure surface of said primary aerofoil element follow a path including over a suction surface of said secondary aerofoil element via said gap, while concurrently providing a trajectory to particulate matter flowing in said at least some streamlines proximate to said pressure surface of said primary aerofoil element to cause said particulate matter to overshoot said gap. 20. The method according to claim 19, comprising aligning said primary aerofoil element at an angle of attack, and aligning said secondary aerofoil element at a deflection angle with respect to the primary aerofoil element, such as to ensure said at least some streamlines proximate to a pressure surface of said primary aerofoil element follow a path to a suction surface of said secondary aerofoil element via said gap, while concurrently providing a trajectory to particulate matter flowing in said at least some streamlines proximate to said pressure surface of said primary aerofoil element such as to cause said particulate matter to overshoot said gap. 21. The method according to claim 20, wherein said angle of attack and said deflection angle are such as to enable said primary aerofoil element to effectively shield the secondary aerofoil element from said particulate matter. 22. The method according to claim 20, wherein said angle of attack is non-positive, and said deflection angle is positive. 23. A method for designing a two element aerofoil comprising a primary aerofoil element including a leading edge of the aerofoil and a secondary aerofoil element including a trailing edge of the aerofoil, and a gap therebetween, the method comprising generating an aerofoil profile to ensure that at least some streamlines proximate to a pressure surface of said primary aerofoil element follow a path including over a suction surface of said secondary aerofoil element via said gap, while concurrently providing a trajectory to particulate matter flowing in said at least some streamlines proximate to said pressure surface of said primary aerofoil element such as to cause said particulate matter to overshoot said gap.