A light aircraft of mass kg with wing area m cruises straight and level at m s…

PHYSICS · Subjective · Fermi University Physics · Fluids & Continuum Physics · Kinematics, conservation laws and ideal flow · Kinematics, conservation laws and ideal flow

Fluids and Continuum Physics, Ch Bernoulli at work: Venturi meters, Pitot tubes and lift

Problem

A light aircraft of mass

1500

kg with wing area

20

^2

cruises straight and level at

60

m s

^{-1}

through air of density

1.2

kg m

^{-3}

. Take

g = 9.8

m s

^{-2}

and assume the wing carries the whole weight. The lift coefficient is defined by

L = C_L\,\tfrac12\rho U^2 S

, with

S

the wing area and

U

the flight speed. What lift coefficient does the aircraft need?

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