For a level flight at cruise altitude, $C_{D}=0.018$ with drag coefficient at zero lift, $C_{D, 0}=0.015 .$ For a $30^{\circ}$ climb at the same altitude and speed,

For a level flight at cruise altitude, $C_{D}=0.018$ with drag coefficient at zero lift, $C_{D, 0}=0.015 .$ For a $30^{\circ}$ climb at the same altitude and speed,

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