Fundamentos de Engenharia Aeronáutica - Volume único

82
L( y)
= ρ ⋅ v ⋅ Γ ( y)
L ( y)
= 1,225 ⋅ 23 ⋅ 0
L( y)
= 0 N/m
Para y = -1,00m,
A circulação é dada por:
⎛ 2 ⋅ y ⎞
Γ ( y)
= Γ
0
⋅ 1 − ⎜ ⎟
⎝ b ⎠
2
⎛ 2 ⋅ ( −1,00)
⎞
Γ ( y)
= 5,425 ⋅ 1 − ⎜ ⎟
⎝ 2,5 ⎠
Γ ( y)
= 3,255 m²/s
E a força de sustentação é:
L( y)
= ρ ⋅ v ⋅ Γ ( y)
L ( y)
= 1,225 ⋅ 23 ⋅ 3,255
L( y)
= 91,70 N/m
Para y = -0,75m,
A circulação é dada por:
2
⎛ 2 ⋅ y ⎞
Γ ( y)
= Γ
0
⋅ 1 − ⎜ ⎟
⎝ b ⎠
2
⎛ 2 ⋅ ( −0,75)
⎞
Γ ( y)
= 5,425 ⋅ 1 − ⎜ ⎟
⎝ 2,5 ⎠
Γ ( y)
= 4,340 m²/s
E a força de sustentação é:
L( y)
= ρ ⋅ v ⋅ Γ ( y)
L ( y)
= 1,225 ⋅ 23 ⋅ 4,340
L( y)
= 122,27 N/m
2