Detailed Example of Aircraft Performance Calculations: Climb ...
Detailed Example of Aircraft Performance Calculations: Climb ...
Detailed Example of Aircraft Performance Calculations: Climb ...
Create successful ePaper yourself
Turn your PDF publications into a flip-book with our unique Google optimized e-Paper software.
<strong>Aircraft</strong> <strong>Climb</strong> <strong>Performance</strong>8000 m (26,200 feet) and 290 knots IAS• The true mach number is 0.6512, the speed <strong>of</strong> sound is 308.0 m/s and the density <strong>of</strong> air is 0.524 k/cu. m.• The true airspeed (TAS) is 200.8 m/s or 390 knots•The lift coefficient needed to maintain flight at 200.63 m/s is,C l= 2mgρV 2 S = 2 *(540,000)(9.81)(0.524)(200.8) 2 (858)• The drag coefficient at 26,200 feet and 290 knots (IAS) can becalculated using the standard parabolic drag polar modelC d= C do+ C di= C do+• Note that the value <strong>of</strong> C do at Mach 0.6512 is 0.020Virginia Tech - Air Transportation Systems Laboratory(kg)(m / s 2 )(kg / m 3 )(m / s)(m 2 ) = 0.5844C 2lπ ARe = 0.020 + 0.5844 2π(9.0)(0.84) = 0.0344 17
Change language