Detailed Example of Aircraft Performance Calculations: Climb ...

Aircraft Climb Performance2,000 feet and 210 knots IAS• The total drag is,D = 1 2 ρV 2 SC d= 1 2 (1.156)(110.42)2 (858)(0.0523) = 316,340N• The calculated drag has units of Newtons (verify by yourself)• The thrust produced by all 4 engines in the very large capacitytransport is estimated using the simple linear modelT 0,M= T 0,M =0− λM trueT h,M= T 0,M⎛ ρ h⎝⎜ ρ 0⎞⎠⎟m• The first expression estimates the thrust at sea level (hencesubscript 0) at any mach number• The second expression corrects the thrust developed for any altitude(h)Virginia Tech - Air Transportation Systems Laboratory11