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An airplane's wing lift coefficient is given by the formula: 1 CL= 0.1(a+1deg) deg where a is the angle of attack. The necessary angle

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An airplane's wing lift coefficient is given by the formula: 1 CL= 0.1(a+1deg) deg where a is the angle of attack. The necessary angle of attack to keep a level flight at the start of a cruise is 1deg. Provide the necessary angle of attack to keep a level flight at the end of the cruise when the weight of the plane has reduced to half. Provide your answer in degrees.

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