Page:Aerial Flight - Volume 1 - Aerodynamics - Frederick Lanchester - 1906.djvu/282

columns; both Tables IV. and V. being values of $\beta$ appropriate to least gliding angle, that is, for $\gamma =$ minimum.

Table V.

Values of $\beta _{1}$ (continued).

$n.$	$\xi =$ .025	$\xi =$ .020	$\xi =$ .015	$\xi =$ .010
3 4 5 6 7 8 — 10 — 12	.210 = 12.0° .219 = 12.5° .226 = 12.9° .230 = 13.2° .236 = 13.5° .244 = 14:0° — .256 = 14.7° — .268 = 15.3°	.189 = 10.8° .196 = 11.2° .202 = 11.6° .206 = 11.8° .212 = 12:15° .218 = 12:5° — .228 = 13:0° — .239 = 13.7°	.163 = 9.3° .169 = 9.7° .174 = 10.0° .178 = 10.2° .183 = 10:5° .189 = 10.8° — .198 = 11:3° — .207 = 11.8°	.133 = 7.6° .138 = 7.9° .142 = 8.1° .145 = 8:3° .149 = 8:5° .154 = 8.8° — .161 = 9:2 — .169 = 9.7°

Table VI.

Least Gliding Angle ($=\gamma _{1}$) (Theoretical).

Minimum value of $\gamma$ or $\gamma _{1}=(1-\epsilon )\ {\sqrt {\frac {2\ \xi \ C}{\kappa \ (1-\epsilon ^{2})}}}$

$n.$	$\xi =$ .030		$\xi =$ .025		$\xi =$ .020		$\xi =$ .015		$\xi =$ .010
3 4 5 6 7 8 — 10 — 12	6.85° 6.32° 5.8° 5.5° 5.2° 4.8° — 4.5° — 4.2°	1:8.3 1:9 1:10 1:10.4 1:11 1:12 — 1:12.8 — 1:13.7	6.25° 5.75° 5.3° 5.0° 4.7° 4.5° — 4.1° — 3.8°	1:9.2 1:10 1:10.8 1:11.5 1:12.2 1:12.8 — 1:14 — 1:15	5.6° 5.15° 4.75° 4.5° 4.25° 4.0° — 3.65° — 3.42°	1:10.2 1:11.1 1:12 1:12.8 1:13.5 1:14.4 1:15.8 — 1:16.8	4.8° 4.4° 4.1° 3.9° 3.6° 3.4° — 3.2° — 3.0°	1:12 1:13 1:14 1:14.7 1:15.9 1:16-8 — 1:17.9 — 1:19	3.95° 3.65° 3.40° 3.20° 3.00° 2.80° — 2.60° — 2.40°	1:14.5 1:15.7 1:16.8 1:17.9 1:19.1 1:20.5 — 1:22 — 1:23.9

Table VI. gives the theoretical values of $\gamma$ corresponding to the ascertained values of $\beta$, that is to say, this Table represents the theoretical minimum gliding angle for the values of $\xi$ employed.

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