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Use following data of an aircraft at SLfor solving questions

`4&5`

: Wing Parameters

```
Wing Parameters H. Tail Parameters
AR =8,AR=5.5
\lambda =1.0,\lambda =1.0
S=18m^(2),S=3.5m^(2)
V=5=0.
```

Other Parameters

`AR=5.5`

`\lambda =1.0`

`S=3.5m^(2)`

`V=95(m)/(s)`

`x_(se)=0.25c`

`x_(cB)=0.3c`

`W=35000N`

`I_(2)=2000kg-m^(2)`

`\tau =0.5`

`i=2`

deg

`V=85(m)/(s)`

`(C_(m_(e)))_(frucluec )=-(0.005)/(r)ad`

`C_(L_(0))=0.31`

`i=-2deg`

`(C_(m_(Q)))_(twurches )=(0.10)/(r)adS_(D_(0))=0.03`

`C_(R_(Q))=-(0.005)/(r)adC_(L_(Se ))=(0.25)/(r)ad`

`C_(x_(u))=-0.17`

`C_(h_(se))=-(0.004)/(r)ad,L_(1)=5m`

`C_(L_(\alpha ))=(5)/(r)ad`

`C_(L_(a))=(4)/(r)ad`

`C_(z_(d))=-(2.6)/(r)ad`

`C_(m_(ac))=-0.12`

`C_(m_(ac))=0.0`

`C_(h_(0))=0`

`C_(Z_(4))=(7.5)/(r)ad`

4. Calculate

`C_(m_(l))`

and

`C_(m_(g))`

contribution and Neutral point from above data for stick fixed and

`(4,4,2)+`

`(3,3,2)`

5. stick free case. 6. Calculate

`x_(u),Z_(w),M_(a),M_(q)`

and

`M\alpha `

. 2.5

`5\times 1`

`(2,2)`