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Low speed airfoil design for aerodynamic improved performance of UAVs

An airfoil and low-speed technology, applied to the direction of wings, motor vehicles, wing shapes, etc., can solve problems such as increasing difficulty

Active Publication Date: 2017-04-05
THE BOEING CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

high camber also increases the difficulty of including the structural components necessary to integrate the deployable (folding) wings into the fuselage

Method used

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  • Low speed airfoil design for aerodynamic improved performance of UAVs
  • Low speed airfoil design for aerodynamic improved performance of UAVs
  • Low speed airfoil design for aerodynamic improved performance of UAVs

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Experimental program
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Embodiment Construction

[0017] figure 2 is a perspective view of an unmanned aerial vehicle (UAV) 100 . UAV 100 includes airframe 102 and propulsion unit 104 , which may be coupled to airframe 102 directly or indirectly. That is, in some embodiments, propulsion unit 104 may be coupled to wing or airfoil 106 , or in other embodiments, propulsion unit 104 may be coupled directly to fuselage 102 . In other embodiments, multiple propulsion units 104 may be coupled to the airfoil 106 . Airfoil 106 is configured to enhance the performance of UAV 100 relative to lift at zero angle of attack and to reduce drag on the lower surface of airfoil 106 , as discussed in more detail below.

[0018] image 3 is a cross-section of the airfoil 106 according to the present disclosure. Airfoil 106 includes an upper surface 120 and a lower surface 122 . Leading edge 124 is driven into the oncoming air by the motion of UAV 100 . Trailing edge 126 is located opposite leading edge 124 where upper surface 120 meets lowe...

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Abstract

The invention relates to a low speed airfoil design for aerodynamic improved performance of UAVs. An airfoil (105) configured for low speed performance in an unmanned aerial vehicle (100) includes an upper surface (120) having an upper surface portion (164) with a top local surface angle magnitude of less than 5 degrees at a subsection (168) of a chord (128) and a lower surface (122) having a lower surface portion with a bottom local surface (122) angle magnitude of less than 5 degrees at the subsection of the chord. The chord (128) is defined by a line starting at a leading edge (124) of the airfoil (106) and extending to a trailing edge (126) of the airfoil (106).

Description

technical field [0001] The present disclosure relates generally to airfoils for use in aircraft, and more particularly to airfoil designs suitable for unmanned aerial vehicles. Background technique [0002] Some aircraft designs, particularly unmanned aerial vehicles, use complex wing or airfoil shapes for improved low speed performance. These airfoils typically exhibit severe stall characteristics that prevent the aircraft from operating in a full range of conditions. Further, these complex shapes are difficult to manufacture, have limited internal volume, and can be difficult to attach external components such as trailing edge flaps. [0003] A side view of a prior art airfoil 10 is shown in FIG. 1 . Airfoil 10 has an upper surface 12 and a lower surface 14 . To achieve good performance at low speeds, the airfoil 10 is characterized by complex curvatures that add both structural weight and manufacturing complexity. The thin trailing edge 16 makes it difficult or imposs...

Claims

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Application Information

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IPC IPC(8): B64C3/10B64C3/14
CPCB64C3/10B64C3/14B64C2003/146B64C2003/147B64C2003/143B64U10/25B64U30/12B64U20/70Y02T50/10B64C3/34
Inventor B·M·霍平T·M·加勒特
Owner THE BOEING CO
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