1.

The overall drag coefficient of an aircraft of weight W and wing area S is given by CD=a+bC2LWhere 'a' and 'b' are constants. The maximum drag in horizontal flight will be

Answer»

The overall drag coefficient of an aircraft of weight W and wing area S is given by



CD=a+bC2L



Where 'a' and 'b' are constants. The maximum drag in horizontal flight will be



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