Given that an engine's rated power is 160 HP (~119kW), how can I express thrust (T) in newtons, if aerodynamic drag (D) requires weight expressed in newtons as well to ensure consistency when calculating power available (Pa) and power required (Pr)?:(adsbygoogle = window.adsbygoogle || []).push({});

[itex]D = (\frac{1}{2}\rho SC_{D})V^{2}+\frac{2W^2}{\rho S\pi AV^2}[/itex]

where:

[itex]\rho[/itex] = density at given altitude, [itex]\frac{kg}{m^3}[/itex]

[itex]S[/itex] = wing area, [itex]m^2[/itex]

[itex]C_{D}[/itex] = zero-lift coefficient of drag

[itex]V[/itex] = true airspeed, [itex]\frac{m}{s}[/itex]

[itex]A[/itex] = wing aspect ratio

I want to solve the equation for excess power: [itex]P_{ex} = P_{a} - P_{r} = TV - DV[/itex]

Thank you!

Rustam

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# Thrust in Newtons (aviation)

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