A wing and tail are geometrically similar, while tail area is one-third of the wing area and distance between two aerodynamic centres is equal to wing semi-span $(b / 2) .$ In addition, following data is applicable:

$\epsilon_{\alpha}=0.3, C_{L}=1.0, C_{L_{\alpha}}=0.08 / \operatorname{deg} ., \bar{c}=2.5 m, b=30 m, C_{M_{a c}}=0, \eta_{t}=1 .$ The symbols have their usual aerodynamic interpretation.

The angle of incidence of tail to trim the wing-tail combination for a $5 \%$ static margin is

(A) $-1.4^{\circ}$

(B) $-0.4^{\circ}$

(C) $0.4^{\circ}$

(D) $1.4^{\circ}$

A wing and tail are geometrically similar, while tail area is one-third of the wing area and distance between two aerodynamic centres is equal to wing semi-span $(b / 2) .$ In addition, following data is applicable:

$\epsilon_{\alpha}=0.3, C_{L}=1.0, C_{L_{\alpha}}=0.08 / \operatorname{deg} ., \bar{c}=2.5 m, b=30 m, C_{M_{a c}}=0, \eta_{t}=1 .$ The symbols have their usual aerodynamic interpretation.

The angle of incidence of tail to trim the wing-tail combination for a $5 \%$ static margin is

(A) $-1.4^{\circ}$

(B) $-0.4^{\circ}$

(C) $0.4^{\circ}$

(D) $1.4^{\circ}$

A thin long circular pipe of $10 \mathrm{~mm}$ diameter has porous walls and spins at 60 rpm about its own axis. Fluid is pumped out of the pipe such that it emerges radially relative to the pipe surface at a velocity of $1 \mathrm{~m} / \mathrm{s}$. [Neglect the effect of gravity.]

What is the radial component of the fluid's velocity at a radial location $0.5 \mathrm{~m}$ from the pipe axis?

(A) $0.01 \mathrm{~m} / \mathrm{s}$

(B) $0.1 \mathrm{~m} / \mathrm{s}$

(C) $1 \mathrm{~m} / \mathrm{s}$

(D) $10 \mathrm{~m} / \mathrm{s}$

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