Lancair Evolution Performance

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Given: A spec sheet was given for the Lancair Evolution giving a number of dimensions, weights, performance details, and limiting and recommended speeds. This information can be used to determine the performance characteristics of the aircraft, giving basic flight and control characteristics. More specifically for this performance evaluation the coefficients of lift and drag will be determined at a number of specifics points. Find: More specifically the class was supposed to find the following coefficients at 4 condition or power settings. Then the class is asked to evaluate these values and determine if the values make sense and if there are any abnormalities. Determine CL, D, CD, CDi, CDo, L/D in cruise at 4 conditions (power settings), Calculate the contributions of skin friction to CDo in each of the above conditions, Determine CLmax with and without flaps, Determine CLmaxL/D, CLminPR . Plot CDi, CDo, CD, CLmax on a graph as a function of CL What else can you determine with the takeoff distance provided? Assumptions: Assume steady level flight at the given power setting. Assume that Swet was twice the wing area and the area of the fuselage and tail was approximately a cylinder with a diameter of 10 ft and a length of 30 ft. It was determined that this gave a relatively close estimate for the surface area of the aircraft. Assume that the propeller efficiency (ηp) is 0.8, which is a typical efficiency for general aviation aircrafts. Assume the density of air at 28,000 ft is 0.000958 slugs/cubic-foot, which can be determined using an online atmospheric calculator. Assume the viscosity of air at 28,000 ft is 3.15E-7 pounds-force second/square-foot, which can also be determined using an online atmospheric calculator. Assume that the power provided by the engine is 787 Hp, which can be determined by researching the Pratt

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