Table 2.

BEM calculations for the airfoil Eppler design (E63).

S	$r_i$(m)	${\lambda }_{r,i}$	$U_{\mathit{blade}}\left(\frac{{\text{m}}^2}{\text{s}}\right)$	$W_{\mathit{rel}}\left(\frac{\text{m}}{\text{s}}\right)$	${\varnothing }_i(\text{deg})$	${\propto }_{\mathit{design}}(\text{deg})$	${\beta }_i$	Chord $C_i\left(\text{m}\right)$
1	0.02	0.125	0.839	7.586	55.25	5	50.25	0.062
2	0.06	0.375	2.516	7.949	46.296	5	41.296	0.133
3	0.1	0.625	4.194	8.628	38.663	5	33.663	0.158
4	0.14	0.875	5.872	9.556	32.543	5	27.543	0.158
5	0.18	1.125	7.549	10.67	27.756	5	22.756	0.149
6	0.22	1.375	9.227	11.916	24.018	5	19.018	0.137
7	0.26	1.625	10.904	13.257	21.072	5	16.072	0.125
8	0.3	1.875	12.582	14.668	18.715	5	13.715	0.114
9	0.34	2.125	14.26	16.13	16.801	5	11.801	0.104
10	0.38	2.375	15.937	17.631	15.222	5	10.222	0.096
11	0.42	2.625	17.615	19.161	13.903	5	8.903	0.089
12	0.46	2.875	19.292	20.713	12.786	5	7.786	0.082
13	0.5	3.125	20.97	22.284	11.83	5	6.83	0.076
14	0.54	3.375	22.648	23.87	11.003	5	6.003	0.071
15	0.58	3.625	24.325	25.467	10.281	5	5.281	0.067
16	0.62	3.875	26.003	27.074	9.647	5	4.647	0.063
17	0.66	4.125	27.68	28.689	9.085	5	4.085	0.06
18	0.7	4.375	29.358	30.311	8.583	5	3.583	0.056
19	0.74	4.625	31.036	31.938	8.134	5	3.134	0.054
20	0.78	4.875	32.713	33.571	7.728	5	2.728	0.051