Detailed Example of Aircraft Performance Calculations: Climb ...
Detailed Example of Aircraft Performance Calculations: Climb ...
Detailed Example of Aircraft Performance Calculations: Climb ...
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<strong>Aircraft</strong> <strong>Climb</strong> <strong>Performance</strong>2,000 feet and 210 knots IAS• The lift coefficient needed to maintain flight is,C l= 2mgρV 2 S = 2 * (540,000)(9.81)(1.1560)(110.42) 2 (858)• The lift coefficient is non-dimensional• The drag coefficient can be calculated using the standardparabolic drag polar modelC d= C do+ C di= C do+(kg)(m / s 2 )(kg / m 3 )(m / s)(m 2 ) = 0.8761C 2lπ ARe = 0.020 + 0.8761 2π(9.0)(0.84) = 0.0523 10• Note that the value <strong>of</strong> Cdo is found by interpolation in the tablefunction relating Cdo and Mach number (Cd is non-dimensional)Virginia Tech - Air Transportation Systems Laboratory
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