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>8000 m (26,200 feet) and 290 knots IAS• The thrust at altitude (h) is then,m⎛ ρT h,M= T h⎞0,M⎝⎜ ρ 0 ⎠⎟T h,M= 235,110 0.5240.96⎛ ⎞⎝⎜1.225 ⎠⎟T h,M= 104,040 Newtons• For four engines the total thrust is,T total= T h,MnT total= 104,040(4) = 416,180 Newtons• Now we can calculate the rate <strong>of</strong> climb at Mach 0.6512 and8,000 metersVirginia Tech - Air Transportation Systems Laboratory19
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