An aeroplane of mass $4.5 \times 10^4 \,kg$ and total wing area of $600 \,m^2$ is travelling at a constant height. The pressure difference between the upper and lower surfaces of its wings is (Acceleration due to gravity $= 10 \,m \,s^{-2}$)

  • A
    $500 \,N \,m^{-2}$
  • B
    $825 \,N \,m^{-2}$
  • C
    $600 \,N \,m^{-2}$
  • D
    $750 \,N \,m^{-2}$

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