For the existing transonic flow = 0.95, a rectangular airfoil with relative thickness t = 0.08 and
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For the existing transonic flow = 0.95, a rectangular airfoil with relative thickness t = 0.08 and aspect ratio λ = 4. If the flow is similar try to calculate the aspect ratio and the relative thickness of the wing at the condition of Ma∞ = 1.07
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