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Determining the drag and the lift slope

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An airplane has a mass of 20,000 kg and flies at 175 m/s at 5000m standard altitude. Its rectangular wing has a 3m chord and a symmetric airfoil at 2.5° angle of attack. Estimate (a) the wing span, (b) the aspect ratio, and (c) the induced drag. Take density of air to be 0.7 Kg/m3. Assume that the factors for induced drag and the lift slope, d and t, respectively, are equal to 0.01; i.e., d = t = 0.01.

Reference no: EM13886249

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