| 发明名称 |
Low Speed Airfoil Design for Aerodynamic Improved Performance of UAVs |
| 摘要 |
An airfoil configured for low speed performance in an unmanned aerial vehicle includes an upper surface having an upper surface portion with a top local surface angle magnitude of less than 5 degrees at a subsection of a chord and a lower surface having a lower surface portion with a bottom local surface angle magnitude of less than 5 degrees at the subsection of the chord. The chord is defined by a line starting at a leading edge of the airfoil and extending to a trailing edge of the airfoil. |
| 申请公布号 |
US2017088260(A1) |
申请公布日期 |
2017.03.30 |
| 申请号 |
US201514865851 |
申请日期 |
2015.09.25 |
| 申请人 |
The Boeing Company |
发明人 |
Hopping Bradley M.;Garrett Timothy M. |
| 分类号 |
B64C39/02;B64C3/34;B64C3/14 |
主分类号 |
B64C39/02 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. An airfoil configured for low speed performance in an unmanned aerial vehicle, the airfoil comprising:
an upper surface having an upper surface portion with a top local surface angle magnitude of less than 5 degrees at a subsection of a chord, wherein the chord is defined by a line starting at a leading edge of the airfoil and extending to a trailing edge of the airfoil; and a lower surface having a lower surface portion with a bottom local surface angle magnitude of less than 5 degrees at the subsection of the chord. |
| 地址 |
Chicago IL US |
