24 AEROPLANE PERFORMANCE CALCULATIONS 



2 



L = -00237^ S(r 4 67V) s ... (3) 

 W/ - L(/' - ^) . (4) 



L = H* (5) 



equation (4) being obtained by taking moments about the 

 c.p. of the tail, neglecting the cosines of small obliquities (see 

 figure). From equation (4) we obtain 



(L/W) 



where 7 = - (7) 



and 8 --..'. . ($) 



From equations (3), (5), and (L/W) we have 



= _i JL^ 



= -00237(1 -467)* L S 



i WL/W 



aL/W 



i W I96W 



-""I wiflA ""j max 



/ V X 2 _ RaL/W 

 \IOO/ = IO,OOOX 



.-. from equation (2) 



/3L/W WL/VV 

 \ T7D~ 



where y8 = i ....... (/3) 



Equations (i), (L/W), (7), (8), (V), (a), (T), and (/5) are in 

 such a form that a tabular method can be conveniently applied 

 to thern (see Chapter XL). 



The values of L/D and k^ max used above are, of course, the 

 corrected values taken from the wing characteristic. 



