The magnitude of stagnation pressure can be derived from Bernoulli equation^[3][1] for incompressible flow and no height changes. For any two points 1 and 2:

${\displaystyle P_{1}+{\tfrac {1}{2}}\rho v_{1}^{2}=P_{2}+{\tfrac {1}{2}}\rho v_{2}^{2}}$ 

The two points of interest are 1) in the freestream flow at relative speed ${\displaystyle v}$  where the pressure is called the "static" pressure, (for example well away from an airplane moving at speed ${\displaystyle v}$ ); and 2) at a "stagnation" point where the fluid is at rest with respect to the measuring apparatus (for example at the end of a pitot tube in an airplane).

Then

${\displaystyle P_{\text{static}}+{\tfrac {1}{2}}\rho v^{2}=P_{\text{stagnation}}+{\tfrac {1}{2}}\rho (0)^{2}}$ 

or^[4]

${\displaystyle P_{\text{stagnation}}=P_{\text{static}}+{\tfrac {1}{2}}\rho v^{2}}$ 

where:

${\displaystyle P_{\text{stagnation}}}$  is the stagnation pressure

${\displaystyle \rho \;}$  is the fluid density

${\displaystyle v}$  is the speed of fluid

${\displaystyle P_{\text{static}}}$  is the static pressure

So the stagnation pressure is increased over the static pressure, by the amount ${\displaystyle {\tfrac {1}{2}}\rho v^{2}}$  which is called the "dynamic" or "ram" pressure because it results from fluid motion. In our airplane example, the stagnation pressure would be atmospheric pressure plus the dynamic pressure.

In compressible flow however, the fluid density is higher at the stagnation point than at the static point. Therefore, ${\displaystyle {\tfrac {1}{2}}\rho v^{2}}$  can't be used for the dynamic pressure. For many purposes in compressible flow, the stagnation enthalpy or stagnation temperature plays a role similar to the stagnation pressure in incompressible flow.^[5]

Stagnation pressure is the static pressure a gas retains when brought to rest isentropically from Mach number M.^[6]

${\displaystyle {\frac {p_{t}}{p}}=\left(1+{\frac {\gamma -1}{2}}M^{2}\right)^{\frac {\gamma }{\gamma -1}}\,}$ 

or, assuming an isentropic process, the stagnation pressure can be calculated from the ratio of stagnation temperature to static temperature:

${\displaystyle {\frac {p_{t}}{p}}=\left({\frac {T_{t}}{T}}\right)^{\frac {\gamma }{\gamma -1}}\,}$ 

where:

${\displaystyle p_{t}}$  is the stagnation pressure

${\displaystyle p}$  is the static pressure

${\displaystyle T_{t}}$  is the stagnation temperature

${\displaystyle T}$  is the static temperature

${\displaystyle \gamma }$  is the ratio of specific heats

The above derivation holds only for the case when the gas is assumed to be calorically perfect (specific heats and the ratio of the specific heats ${\displaystyle \gamma }$  are assumed to be constant with temperature).

• Hydraulic ram
• Stagnation temperature

• L. J. Clancy (1975), Aerodynamics, Pitman Publishing Limited, London. ISBN 0-273-01120-0
• Cengel, Boles, "Thermodynamics, an engineering approach, McGraw Hill, ISBN 0-07-254904-1

• Pitot-Statics and the Standard Atmosphere
• F. L. Thompson (1937) The Measurement of Air Speed in Airplanes, NACA Technical note #616, from SpaceAge Control.