View source for File:Heat transfer to rocket tank.c

Program calculating the heat transferred to a cryogenic tank (typically LOX) for balloon- or air-to-orbit vehicles. Two heat transfer approximations are done.
* when the vehicle is waiting on the ground after tank filling and before it lifts-off from the ground
* during the ascent flight, following configurable climb rates and the ISA atmospheric model already presented here: [[File:ISA_atmospheric_model.c]].

The vaporization rate is given for ground operation, and the overall heat and vaporized mass is given for both.

The atmospheric model is at the beginning of the file, other parameters for flight and tanks are right after it.

Compile with: <code><gcc -o heat_transfer_to_rocket_tank -Wall heat_transfer_to_rocket_tank.c -lm/code>