[Val.gold]

Hello,

I am working on a project which includes an airplane flying in 10000 m in the sky, with a speed of 355 m/s. From the book " Thermodynamics" of sir Yunus A. Cengel. Michael A. Boles i know that in 10000 m i have a temperature = -49.9 Celsius , Pressure = 26500 Pa , Speed of light = 299.5 m/s , Density = 0.414.
While working on Ansys Fluent , using Density Based ( some say it is better to use pressure based cause it works better on supersonic flows, but i think it density works as well ) and im in the pressure inlet i have to give a total pressure and a sueprsonic/ initial gauge pressure ( which u have to give in order to find the velocity etc ).
The total pressure is the sum of dynamic and static pressure.

My problem is this :
The dynamic pressure can be calculated by the formulas there are ( for an example density * the squre of speed , divided by 2 ).

But what is the value of static pressure ? how can I calculate it ?
Is it just the value the book gives ( 26.5 KPa ), which is the atmpospheric pressure if I understand correct ???