spring_spl1 - parenleftBigg parenrightBigg Flight Power...

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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.

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spring_spl1 - parenleftBigg parenrightBigg Flight Power...

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