Fundamentos de Engenharia Aeronáutica - Volume único

279
n
2
2
2
q ⋅T
⋅ S q ⋅ C
D0
⋅ S
= −
(4.148)
2
2
K ⋅W
K ⋅W
n
2
2
q ⎛ T ⎞ q ⋅ C
D0
= ⋅ ⎜ ⎟ −
(4.148a)
K ⋅ ( W ) ⎝W
⎠ K ( W ) 2
S
⋅
S
n
2
⎡
⎢
q
=
⎢ K ⋅
⎣
⎛
T
W
⎤
⎞⎥
⎡
⎢
D0
⋅ ⎜ ⎟ − ⋅
( W ) ⎥ ⎢ ( ) ( )⎥ ⎥ ⎝ ⎠ K ⋅ W W
S ⎦ S S ⎦
⎣
q
2
C
⎤
(4.148b)
n
2
q
=
K ⋅
⎡⎛
⎢⎜
⎞⎤
⎟
D0
( ) ⎢ ( ) ⎥ ⎥ ⎜
−
W W
⎟
S ⎝ S ⎠⎦
⎣
T
W
q ⋅ C
(4.148c)
Derivando-se a Equação (4.148c), tem-se que:
( T )
W 2 ⋅ q ⋅ C
D0
−
⋅ ( W ) ( W ) dq 2
2 ⋅ n ⋅ dn =
(4.149)
K
S K ⋅
S
( T )
W 2 ⋅ q ⋅ CD0
−
K ⋅ ( W ) ( W ) 2
dn
n ⋅ =
(4.149a)
dq 2 ⋅
S 2 ⋅ K ⋅
S
( T )
W q ⋅ CD0
−
K ⋅ ( W ) ( W ) 2
dn
n ⋅ =
(4.149b)
dq 2 ⋅
S K ⋅
S
Substituindo as Equações (4.148c) e (4.149b) na Equação (4.146c), tem-se que:
⎛ q
⎜
⎝ K ⋅
q
K ⋅
⋅
T
W
2
q ⋅ C
−
K ⋅ W S
D0
−1
−
2
q ⋅ C
+
K ⋅ W S
2
( W S) ( ) 2 ⋅ K ⋅ ( W S) ( ) 2
⋅
T
W
−
q
⋅
T
W
⎞ ⎛
−1
+ ⎜
⎟
⎠ ⎝
2
( W S ) 2 ⋅ K ⋅ ( W S) ⎜
K ⋅ ( W S ) K ⋅ ( W S )
q
q
2
⋅ C
⋅
D0
T
W
−
q
2
⋅ C
D0
D0
2
⎞
⎟
= 0
⎠
(4.150)
(4.150a)
1
2
q
⋅
K ⋅
( W S)
⋅
T
W
−1
= 0
(4.150b)
q
2 ⋅ K
( T W )
⋅ ( W S )
= 1
(4.150c)
ou