Editing True airspeed (section)

===Low-speed flight===
At low speeds and altitudes, IAS and CAS are close to [[equivalent airspeed]] (EAS).

<math>\rho_0 (EAS)^2 = \rho (TAS)^2</math>

TAS can be calculated as a function of EAS and air density:

<math>\mathrm{TAS} =\frac { \mathrm{EAS}}{\sqrt{\frac{\rho}{\rho_0}}}</math>

where
:<math>\mathrm{TAS}</math> is true airspeed,
:<math>\mathrm{EAS}</math> is equivalent airspeed,
:<math>\rho_0</math> is the air density at sea level in the [[International Standard Atmosphere]] (15&nbsp;°C and 1013.25 hectopascals, corresponding to a density of 1.225&nbsp;kg/m<sup>3</sup>),
:<math>\rho</math> is the density of the air in which the aircraft is flying.