Calculation of values of
Standard atmosphere according to ISO 2533
with Speed / Machnumber / Altitude
Version 5.30 (Android)
Copyright E.Baeumler, Brunnen 2018
By clicking on Input line a value can be entered. The calculation is executed and displayed on the respective button by clicking the corresponding button. The program calculates values up to 80 km (corresponding to ISO 2533).
Leading parameters for calculation are pressure altitude and kalibrated airspeed (KCAS). So, when changing altitude, KCAS remains constant, the other "speed values" change.
The value in the input line can be deleted by clicking "CLR".
By selecting the button "Basic Values", the values are reset to normal zero.
In the diagram, a state can be selected by pressing (preferably with a pen), the related values are output directly in the display view.
Leave the graph via Exit button.
The program can be terminated by selecting the button "Exit".
The temperature profile over the altitude according to DIN ISO 2533 is not constant decreasing. In the ranges from 20 km to 32 km and 32 km to 47 km positive temperature gradients are defined. In the bands of 11 km to 20 km and 47 km to 51 km temperature is constant. If you enter "temperature values" so undefined spaces may be possible or you have to choose between several possible "height values". This is queried by an entry window.
The program is developed for Smartphones and Tablets. If you find bugs or want improvements, please let me know.
The use of the program is complete at your own risk.
Altitude Pressure Altitude in [ft] or [m]
St.Press Static pressure [hPa]
St.Temp Static Temperature [ C] or [ K]
Sigma Relative density
ft / hPa absolute amount of altitude change / [ft]
Mach Mach number
qc / ps (Dynamic-static pressure) / static pressure
TAS True airspeed [kt] or [m / s]
CAS Calibrated airspeed [kt] or [m / s]
qc pitot - static pressure [hPa]
EAS equivalent airspeed [kt]
Ti Dynamic temperature [ C] or [ K]