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Given aircraft weight of jet plane W is equal to 150 kN. The drag polar CD = 0.02 + 0.0524 C2. The wing area

Given aircraft weight of jet plane W is equal to 150 kN. The drag polar CD = 0.02 +0.0524 C2. The wing area

Given aircraft weight of jet plane W is equal to 150 kN. The drag polar CD = 0.02 + 0.0524 C2. The wing area reference S = 25 m and at sea level condition, the air density p = 1.225 kg/m. Determine The flight speed at the maximum climb angle Vymax

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