Climb Performance Examples with Solutions

Climb Performance Examples Solutions 1. A turbo-fan powered aircraft has a vaporize area of 160 m2 and a drag polar of the form, CD = 0.02 + 0.045CL2. At sea-level, the engines produce a total thrust of cc kN. The aircraft weighs 85,000 kg. a) go under the climb angle and rate of climb at sea-level if the aircraft is flying at a speed of speed of light m/s. [pic] [pic] [pic] [pic] [pic] [pic] [pic] b) Determine the thrust to weight ratio compulsory to maintain a climb gradient of 3% at a speed of 100 m/s. [pic] [pic] [pic] From part a), [pic] [pic] [pic] c) Determine the maximum obtainable climb angle and the speed require to achieve it at sea-level. [pic] Since the thrust operational is 200 kN and this does non depend on speed. The maximum value of T-D occurs at lower limit D. From the graph, the nominal drag is about 50 kN at a speed of 115 m/s.

[pic] Alternatively, we could work out the minimum drag exactly [pic] If we assume [pic], [pic] [pic] For minimum drag, [pic] [pic] [pic] d) Determine the maximum available rate of climb and the speed required to achieve it at sea-level. The maximum rate of climb occurs at the maximum overmuch power. The power available is given by TV, where T is the available thrust (200 kN). From the graph, the maximum excess power is 23000 kW at a speed of about 190 m/s (188.5 is the exact value). [pic] 2. A turbo-prop aircraft has a drag polar with CDo = 0.043 and k = 0.032 based on a wing area of 54 m2. The total engine power is 3200 kW and the propeller ability is 80%. The aircraft weighs of 15,000 kg.... If you want to get a full essay, straddle it on our website: Orderessay

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