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Unformatted text preview: parenleftBigg parenrightBigg Flight Power Relations 9 Feb 06 Lab 1 Lecture Notes Nomenclature c c C C D aircraft drag L aircraft lift W aircraft weight T propeller thrust V ﬂight speed S reference area (wing area) b wing span AR wing aspect ratio L lift coeﬃcient D drag coeﬃcient CDA 0 drag area of non-wing components ℓ wing-airfoil profile lift coeﬃcient d wing-airfoil profile drag coeﬃcient ρ air density t E Ω T η η η P P P thrust power ( ≡ TV ) shaft motor shaft power elec electric power (Volts × Amps) m electric motor eﬃciency p overall propeller eﬃciency ideal ideal propeller eﬃciency R propeller radius c thrust coeﬃcient m motor rotation rate Ω propeller rotation rate λ propeller advance ratio Re chord Reynolds number elec electrical (battery) energy max maximum ﬂight duration Thrust Power Generation of thrust during ﬂight requires the expenditure of power. In steady level ﬂight, T = D , and hence the thrust power is equal to the drag power. P ≡ TV = DV (steady level ﬂight) (1) In steady level ﬂight we also have W = L , which gives the velocity in terms of other relevant parameters. 1 W = L = ρV 2 S C L (2) 2 parenleftBigg parenrightBigg 1 / 2 2 W V = (3) ρS C L The drag power can then be given as follows....
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This note was uploaded on 01/28/2012 for the course AERO 16.01 taught by Professor Markdrela during the Fall '05 term at MIT.
- Fall '05