An aeroplane is flying through the transonic range. As the Mach Number increases the centre of pressure of the wing will move aft. This movement requires:4
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Which statement is correct about a normal shock wave ?4
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Mach buffet occurs:4
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The aft movement of the centre of pressure during acceleration through the transonic range will:4
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In case of supersonic flow retarded by a normal shock wave a high efficiency (low loss in total pressure) can be obtained if the Mach number in front of the shock is4
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An aeroplane, with a C.G. location behind the centre of pressure of the wing can only maintain a straight and level flight when the horizontal tail loading is:4
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How does positive camber of an aerofoil affect static longitudinal stability?4
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If an aeroplane exhibits insufficient stick force per g, this problem can be resolved by installing:4
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The effect on static stability of an aeroplane with a high wing as compared to a low wing is:4
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One method to compensate adverse yaw is:4
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