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First published online February 12, 2007
Journal of Experimental Biology 210, 881-896 (2007)
Published by The Company of Biologists 2007
doi: 10.1242/jeb.02704
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A computational investigation of the three-dimensional unsteady aerodynamics of Drosophila hovering and maneuvering

Ravi Ramamurti* and William C. Sandberg

Laboratory for Computational Physics and Fluid Dynamics, Naval Research Laboratory, Washington, DC 20375, USA


Figure 1
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  		Fig. 1. Schematic of the hovering Drosophila. LWT, RWT, left/right wingtip; LWH, RWH, left/right wing hinge; LWN, RWN, left/right wing normal vector.

 

Figure 2
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  		Fig. 2. Schematic of the Drosophila in the computational coordinate system. Abbreviations as in Fig. 1.

 

Figure 3
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  		Fig. 3. Roll, yaw and pitch sequence of angular rotations of the body.

 

Figure 4
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  		Fig. 4. Angular position of the body during the maneuver.

 

Figure 5
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  		Fig. 5. Angular positions of the wings during the maneuver (from Fry et al., 2003Go). (A) Stroke angle, (B) deviation from the stroke plane and (C) the angle of attack.

 

Figure 6
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  		Fig. 6. Difference in angular positions between the wings during the maneuver. (A) Experimental raw data and (B) filtered data.

 

Figure 7
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  		Fig. 7. Comparison of time history of (A) lift (L) and (B) thrust (T) forces. Gray and white bars indicate downstroke and upstroke, respectively.

 

Figure 8
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  		Fig. 8. Force component and yaw axis directions for a maneuvering Drosophila.

 

Figure 9
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  		Fig. 9. Time history of yaw moment Myaw. (A) Contributions from right and left wings, (B) the total moment and (C) the filtered moment.

 

Figure 10
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  		Fig. 10. Time history of forward force produced by the wings. (A) Contributions from right and left wings, (B) the difference in force and (C) the filtered difference in force.

 

Figure 11
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  		Fig. 11. Time history of (A) differential side force and (B) filtered side force.

 

Figure 12
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  		Fig. 12. Time history of (A) differential lift force and (B) filtered lift force.

 

Figure 13
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  		Fig. 13. Contributions of the forward and side forces to the yaw moment Myaw.

 

Figure 14
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  		Fig. 14. Moment arms for (A) the forward (f) force and (B) side (s) forces.

 

Figure 15
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  		Fig. 15. Distance (D) of the center of pressure from (A) the center of rotation and (B) the wing hinge.

 

Figure 16
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  		Fig. 16. Force vectors (red arrows) on the left and right wings during a hover cycle, t=0.0156 s to 0.0204 s.

 

Figure 17
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  		Fig. 17. Force vectors (red arrows) on the left and right wings at the beginning of the saccade, t=0.0298 s to 0.0346 s.

 

Figure 18
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  		Fig. 18. Force vectors (red arrows) on the left and right wings in the middle of the saccade, t=0.0538 s to 0.0586 s.

 

Figure 19
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  		Fig. 19. Surface pressure contours on the wings during a hover cycle.

 

Figure 20
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  		Fig. 20. Surface pressure distributions during the initial phase of the saccade maneuver. Colour key as in Fig. 19.

 

Figure 21
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  		Fig. 21. Surface pressure distributions during the middle of the saccade maneuver. Colour key as in Fig. 19.

 

Figure 22
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  		Fig. 22. Vorticity generated by the leading and trailing edges of the wings shown by iso-vorticity surface during a hover cycle.

 

Figure 23
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  		Fig. 23. Iso-vorticity surfaces as seen from the back of the fruit fly during hover.

 

Figure 24
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  		Fig. 24. Contours of iso-vorticity shed by the fruit fly during saccade maneuver.

 




© The Company of Biologists Ltd 2007