Table 2.

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

J C̄ L C̄ TΦ (deg.)β (deg.)χ (deg.)CwC+W,tC−W,tC+W,rC−W,r
0 1.15 0.03 135 0 68 14.09 13.99 −0.99 0.10 −1.98 
0.13 1.15 0.04 129 18.5 49.5 12.67 12.56 −0.74 0.11 −1.66 
0.27 1.15 0.08 131 34.5 33.5 12.01 11.89 −0.68 0.12 −1.55 
0.40 1.15 0.14 145 47 21 13.63 13.49 −0.75 0.14 −1.69 
0.53 1.16 0.20 165 53 15 17.57 17.41 −0.97 0.16 −2.05 
J C̄ L C̄ TΦ (deg.)β (deg.)χ (deg.)CwC+W,tC−W,tC+W,rC−W,r
0 1.15 0.03 135 0 68 14.09 13.99 −0.99 0.10 −1.98 
0.13 1.15 0.04 129 18.5 49.5 12.67 12.56 −0.74 0.11 −1.66 
0.27 1.15 0.08 131 34.5 33.5 12.01 11.89 −0.68 0.12 −1.55 
0.40 1.15 0.14 145 47 21 13.63 13.49 −0.75 0.14 −1.69 
0.53 1.16 0.20 165 53 15 17.57 17.41 −0.97 0.16 −2.05 

Φ, β vary with flight speed; αm=46.5°; n=240 s−1 and non-dimensional periodτ c=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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