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• Using the standard expression to estimate the true machnumber <strong>of</strong> the aircraft at altitude,⎡⎧⎪M true= 5⎢⎢⎨⎣⎢⎩⎪ρ 0ρ⎛ ⎡ ⎛⎢1+ 0.2⎝⎜⎝⎜ ⎣V IAS661.52⎞⎠⎟⎤⎥⎦3.5⎞ ⎫−1⎠⎟ +1 ⎪⎬⎭⎪0.286⎤−1⎥⎥⎦⎥• The true mach number is 0.3267, the speed <strong>of</strong> sound at 600meters is 337.96 m/s and the density <strong>of</strong> air is 1.156 k/cu. m.• The true airspeed (TAS) is 110.41 m/s or 214.6 knots• Use the fundamental lift equation to estimate the lift coefficientunder the known flight conditionL = mg = 1 2 ρV 2 SC lVirginia Tech - Air Transportation Systems LaboratoryC l= 2mgρV 2 S9
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