MEM425F11_HW2 - maximum lift coefficient and the maximum...

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Home work #2 (due 10/06/11) Problem I: Consider an aircraft with the following characteristics: Wing span = 35.8 ft. Wing area = 174.0 ft 2 Normal gross weight = 2950 lb Parasite drag coeff. = 0.025 Oswald efficiency factor = 0.8 Propeller efficiency, = 0.8 maximum lift coefficient = 4.0 max-power from engine = 400 hp (indep. of altitude) Sea-level air density = 2.3769*10 -3 slugs ft -3 a. Compute and plot (Thrust_reqd .vs. Velocity) and (Power_reqd .vs. Velocity) in a cruise flight (level, constant velocity, constant altitude) at sea level. b. Determine the minimum velocities enforced by the stall condition (ie., due to
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Unformatted text preview: maximum lift coefficient) and the maximum velocities enforced by the available engine power. c. From these plots determine the minimum required thrust and power, and the corresponding velocities. Denote these velocities by and . d. Compute these (optimal) velocities using appropriate equations from notes or text. e. Repeat (a) and (b) for these altitudes {10,000; 20,000; 30,000} ft. f. Generate and plot and . For smooth plots you need to consider more number of altitudes. Relevance to Program Outcomes a-k : a, k...
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