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WING AND TAIL LOADING

Aim: To design the wing of the aircraft.

 Theory:

Wing Design

Crw =2S w

b w(1− λ)

Ctw = λ Crw

ŷ =bw

6[1+2 λ

1+ λ  ]

 Tail Design:

Vvt = L t ∗S vt b w∗S w

Vht = L t ∗Sh t 

bw∗S w

bvt= √ S vt ∗ AR  

bht= √ Sht ∗ AR  

Crht =2S ht 

b ht (1− λht )

Crvt =2S vt 

b vt (1− λvt )

Ctht = λht Crht

CtVt = λVt CrVt

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ŷht =b ht 

6[1+2 λht 1+ λht 

  ]

ŷvt =

b vt 

6

[ 1+2 λvt 

1+ λvt   ]

čht =2

3C rht [

1+ λ ht + λ ht 2

1+ λ ht   ]

čht =2

3C rvt [

1+ λ vt + λ vt 2

1+ λ vt   ]

Aileron (b = !"#$"% of bw

Aileron (č) = 15-25% of čw

Rudder and Elevator (b) = 50-90% of bw

Rudder and Elevator (č) = 20-50% of čw

Index:Crw = &oot chord of the wing

Ctw= Ti' chord of the wing

Crt= &oot chord of the hori)ontal tail

Ctt= Ti' chord of the hori)ontal tail

CrVt= &oot chord of the vertical tail

CtVt= Ti' chord of the vertical tail

*w= *+rface area of the wing

*vt= *+rface area of the wing

*ht= *+rface area of the wing

bw= *'an of the wing

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bvt = *'an of vertical tail

bht = *'an of hori)ontal tail

λ = Ta'er ratio of the wingλht = Ta'er ratio of hori)ontal tail

λVt = Ta'er ratio of vertical tail

ŷ = ,ocation of centre of gravity

ŷht = ,ocation of centre of gravity of hori)ontal tail

ŷVt = ,ocation of centre of gravity vertical tail

Vvt = Vertical tail vol+me ratio

Vht = ori)ontal tail vol+me ratio

,t = ,ength of the tail

čht= mean chord of hori)ontal tail

čvt= mean chord of vertical tail