Table 1.

Mean lift(C̄L) and thrust(C̄T) coefficients,midstroke angle of attack αm, stroke plane angle β, body angle χ and coefficient of work per cycle Cwas functions of advance ratio J

J C̄ L C̄ Tαm (deg.)β (deg.)χ (deg.)CwC+W,tC−W,tC+W,rC−W,r
0 1.16 0.03 36 0 68 12.91 12.51 −0.75 0.40 −1.82 
0.13 1.16 0.04 32 16.5 51.5 11.50 10.90 −0.46 0.60 −1.40 
0.27 1.16 0.09 34 29 39 11.47 10.93 −0.43 0.53 −1.32 
0.40 1.15 0.15 43.5 45.5 22.5 13.58 13.37 −0.70 0.21 −1.69 
0.53 1.15 0.20 56 60 8 18.21 18.16 −0.93 0.05 −1.80 
J C̄ L C̄ Tαm (deg.)β (deg.)χ (deg.)CwC+W,tC−W,tC+W,rC−W,r
0 1.16 0.03 36 0 68 12.91 12.51 −0.75 0.40 −1.82 
0.13 1.16 0.04 32 16.5 51.5 11.50 10.90 −0.46 0.60 −1.40 
0.27 1.16 0.09 34 29 39 11.47 10.93 −0.43 0.53 −1.32 
0.40 1.15 0.15 43.5 45.5 22.5 13.58 13.37 −0.70 0.21 −1.69 
0.53 1.15 0.20 56 60 8 18.21 18.16 −0.93 0.05 −1.80 

αm, β vary with flight speed; stroke amplitudeΦ=150°; stroke frequency n=240 s−1 and non-dimensional period τc=8.42.

C+W,t and C−W,t, coefficients of positive and negative work for translation, respectively; C+W,r and C−W,r, coefficients of positive and negative work for rotation, respectively.

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