The wing of a military aircraft has a maximum lift coefficient of 1.25 and an area of 16 m^2; the maximum maneuver load factor is 6.0. If the weight of the aircraft is 50 kN, determine the angle of bank required at a speed of 180 m/s. Calculate also the radius of turn. Take ρ = 1.223 kg/m^3.

Question

The wing of a military aircraft has a maximum lift coefficient of 1.25 and an area of [latex]16 m ^{2}[/latex]; the maximum maneuver load factor is 6.0. If the weight of the aircraft is 50 kN, determine the angle of bank required at a speed of 180 m/s. lculate also the radius of turn. Take [latex]\rho=1.223 kg / m ^{3}[/latex].

Accepted Answer

The maximum available lift is given by

[latex]L_{\max }=(1 / 2) ho V^{2} S C_{ L , \max }[/latex]

that is,

[latex]L_{\max }=(1 / 2) imes 1.223 imes 180^{2} imes 16 imes 1.25=396.3 kN[/latex]

Then,

[latex]n=(396.3 / 50)=7.9[/latex]

which means that the aircraft exceeds the maximum maneuver load at the point of maximum lift. The maneuver load factor is therefore the critical criterion. From Eq. (13.20),

[latex]n=\sec \phi[/latex] (13.20)

[latex]\sec \phi=6.0[/latex]

which gives

[latex]\phi=80.4^{\circ}[/latex]

Then, from Eq. (13.21),

[latex] an \phi=\frac{V^{2}}{g R}[/latex] (13.21)

[latex] an 80.4^{\circ}=\left(180^{2} / 9.81 R ight)[/latex]

So that

[latex]R=558.6 m[/latex]

Question 13.6: The wing of a military aircraft has a maximum lift coefficie...

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