The lift coefficient (CL) of an aeroplane in steady horizontal flight is 0.35. An increase in angle of attack of 1 degree would increase CL by 0.079. If a vertical gust instantly changes the angle of attack by 2 degrees, the load factor will be:4
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Which definition of propeller parameters is correct?4
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In twin-engine aeroplanes with right turning propellers4
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Which one of the following statements about Bernoulli's theorem is correct?4
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The unit of density is:4
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The angle of attack of a wing profile is defined as the angle between:4
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The terms 'q' and 'S' in the lift formula are:4
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The relationship between induced drag and the aspect ratio is:4
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The aeroplane drag in straight and level flight is lowest when the:4
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Which line represents the total drag line of an aeroplane?4
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