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9 results for “aerodynamics”

Formulae (9)

F_D = \tfrac{1}{2}\rho v^2 C_D A

Aerodynamic drag on a moving body.

L = \tfrac{1}{2}\rho v^2 S C_L

Aerodynamic lift produced by a wing depends on air density, speed squared, area and lift coefficient.

D = \tfrac{1}{2}\rho v^2 S C_D

Aerodynamic drag force on the aircraft, analogous to lift with a drag coefficient.

V_s = \sqrt{\dfrac{2W}{\rho S C_{L,max}}}

Minimum speed for level flight, set by maximum lift coefficient.

Re = \dfrac{\rho v L}{\mu}

Ratio of inertial to viscous forces; characterises airflow over an airfoil.

C_L = \dfrac{2L}{\rho v^2 S}

Non-dimensional lift, obtained by rearranging the lift equation.

C_{D,i} = \dfrac{C_L^2}{\pi e AR}

Drag due to lift, decreasing with higher aspect ratio and span efficiency.

n = \frac{L}{W}

Ratio of lift to weight, felt as g-force.

M = \frac{v}{a}

Ratio of speed to the local speed of sound.