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1. 发明申请

US20080283674A1 Low-drag swept wings 有权
标题翻译：低拖风扫翅膀
公开(公告)号：US20080283674A1
公开(公告)日：2008-11-20
申请号：US12007079
申请日：2008-01-07
申请人： Michael Shepshelovich , Anthony-Samuel Sznabel , David-Eli Levy
发明人： Michael Shepshelovich , Anthony-Samuel Sznabel , David-Eli Levy
IPC分类号： B64C3/14
CPC分类号： B64C3/14 , B64C2003/146 , Y02T50/12
摘要： The invention relates to an aircraft, and a method for operating an aircraft, the aircraft having a longitudinally unstable configuration and swept wings, the swept wings being based on aerofoils having a leading edge and configured for preventing attachment line transition in conditions of laminar flow over the swept wing for at least a predetermined first range of lift coefficients at a second range of Reynolds numbers. The invention also relates to an aerofoil, and to a method for providing an aerofoil, the airfoil being configured for a thick-sectioned subsonic/transonic swept wing, having a curved leading edge, a trailing edge, a thickness dimension and a chord dimension, wherein the leading edge comprises a leading edge curvature associated with a leading edge radius that is configured for preventing attachment line transition in conditions of laminar flow over the swept wing.
摘要翻译：本发明涉及一种飞行器以及一种用于操作飞行器的方法，该飞行器具有纵向不稳定的构型和扫掠翼，该扫掠翼基于具有前缘的机翼，并被构造用于防止在层流状态下的连接线转换所述扫掠翼在雷诺数的第二范围处至少提供预定的升力系数的第一范围。本发明还涉及一种机翼，以及一种用于提供机翼的方法，所述翼型件被配置用于具有弯曲前缘，后缘，厚度尺寸和弦弦尺寸的厚切片亚音速/跨音速扫掠翼，其中所述前缘包括与前缘半径相关联的前缘曲率，所述前缘半径被构造成用于防止在所述扫掠翼上层流的条件下的附着线转换。

2. 发明授权

US08113462B2 Low-drag swept wings 有权
标题翻译：低拖风扫翅膀
公开(公告)号：US08113462B2
公开(公告)日：2012-02-14
申请号：US12007079
申请日：2008-01-07
申请人： Michael Shepshelovich , Anthony-Samuel Sznabel , David-Eli Levy
发明人： Michael Shepshelovich , Anthony-Samuel Sznabel , David-Eli Levy
IPC分类号： B64C3/14
CPC分类号： B64C3/14 , B64C2003/146 , Y02T50/12
摘要： The invention relates to an aircraft, and a method for operating an aircraft, the aircraft having a longitudinally unstable configuration and swept wings, the swept wings being based on aerofoils having a leading edge and configured for preventing attachment line transition in conditions of laminar flow over the swept wing for at least a predetermined first range of lift coefficients at a second range of Reynolds numbers. The invention also relates to an aerofoil, and to a method for providing an aerofoil, the airfoil being configured for a thick-sectioned subsonic/transonic swept wing, having a curved leading edge, a trailing edge, a thickness dimension and a chord dimension, wherein the leading edge comprises a leading edge curvature associated with a leading edge radius that is configured for preventing attachment line transition in conditions of laminar flow over the swept wing.
摘要翻译：本发明涉及一种飞行器以及一种用于操作飞行器的方法，该飞行器具有纵向不稳定的构型和扫掠翼，该扫掠翼基于具有前缘的机翼，并被构造用于防止在层流状态下的连接线转换所述扫掠翼在雷诺数的第二范围处至少提供预定的升力系数的第一范围。本发明还涉及一种机翼，以及一种用于提供机翼的方法，所述翼型件被配置用于具有弯曲前缘，后缘，厚度尺寸和弦弦尺寸的厚切片亚音速/跨音速扫掠翼，其中所述前缘包括与前缘半径相关联的前缘曲率，所述前缘半径被构造成用于防止在所述扫掠翼上层流的条件下的附着线转换。

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