Morphology, kinematics and results for acceleration-compensated experiments
| Loaded mass m (kg) | 0.483±0.027 |
| Wing span b (m) | 0.660±0.01 |
| Frequency f (Hz) | 8.02±0.69 |
| Flight velocity V (m s-1) | 4.46±0.27 |
| Tail angle of attack \(\overline{{\alpha}_{\mathrm{tail}}}\) (deg.) | 47.6±6.4 |
| Inclination of wing stroke plane β (deg.) | 35.1±2.6 |
| Tail area Stail (m2) | 0.0204±0.0020 |
| Differential pressure: inner tail (Pa) | 18.2±1.0 |
| Differential pressure: outer tail (Pa) | 32.9±4.5 |
| Differential pressure: mean \(\overline{\mathrm{d}P_{\mathrm{tail}}}\) (Pa) | 25.6±8.5 |
| Weight support % | 7.91±2.5 |
| Direct power (W) | 1.70±0.2 |
| Body mass specific power (W kg-1) | 3.68±0.58 |
| Muscle mass specific power (W kg-1) | 19.3±3.0 |
\(\overline{C_{\mathrm{R,tail}}}\) | 2.14 |
\(\overline{C_{\mathrm{L,tail}}}\) | 1.44 |
\(\overline{C_{\mathrm{D,tail}}}\) | 1.59 |
| Loaded mass m (kg) | 0.483±0.027 |
| Wing span b (m) | 0.660±0.01 |
| Frequency f (Hz) | 8.02±0.69 |
| Flight velocity V (m s-1) | 4.46±0.27 |
| Tail angle of attack \(\overline{{\alpha}_{\mathrm{tail}}}\) (deg.) | 47.6±6.4 |
| Inclination of wing stroke plane β (deg.) | 35.1±2.6 |
| Tail area Stail (m2) | 0.0204±0.0020 |
| Differential pressure: inner tail (Pa) | 18.2±1.0 |
| Differential pressure: outer tail (Pa) | 32.9±4.5 |
| Differential pressure: mean \(\overline{\mathrm{d}P_{\mathrm{tail}}}\) (Pa) | 25.6±8.5 |
| Weight support % | 7.91±2.5 |
| Direct power (W) | 1.70±0.2 |
| Body mass specific power (W kg-1) | 3.68±0.58 |
| Muscle mass specific power (W kg-1) | 19.3±3.0 |
\(\overline{C_{\mathrm{R,tail}}}\) | 2.14 |
\(\overline{C_{\mathrm{L,tail}}}\) | 1.44 |
\(\overline{C_{\mathrm{D,tail}}}\) | 1.59 |
Values are means ± s.d. (N=3).
The muscle mass used for the muscle mass specific power calculation is that of the pair of pectoralis muscles (18% body mass); while the power costs here are due to the tail, they are largely `paid' for by the wing-flapping musculature.