Consider an airplane cruising at an altitude of 10 km where standard atmospheric conditions are 250C and

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Consider an airplane cruising at an altitude of 10 km where standard atmospheric conditions are 250°C and 26.5 kPa at a speed of 800 km/h. Each wing of the airplane can be modeled as a 25-m × 3-m flat plate, and the friction coefficient of the wings is 0.0016. Using the momentum-heat transfer analogy, determine the heat transfer coefficient for the wings at cruising conditions.

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