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 thrust developed by each engine is a linear function <strong>of</strong> machnumber. At sea level and Mach 0.3267 the thrust is,T 0,M= T 0,M =0− λM trueT 0,M= 338,000 − 175,560M trueT 0,M= 338,000 − 175,560(0.3267)T 0,M= 280,646 Newtons• The thrust at altitude (h) is then,T h,M= T 0,M⎛ ρ h⎝⎜ ρ 0T•h,M= 265, 450 Newtons⎞⎠⎟T h,M= 280,646 1.1560.96⎛ ⎞⎝⎜1.225⎠⎟mVirginia Tech - Air Transportation Systems Laboratory14
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