Hi /sci/. I'm an aerospace engineering from france and working on this side project in my lost hours. Please excuse my bad english.

The goal is simple: using what I learned + the internet, I will design a turbojet for middle-sized drones. Design point conditions are the following:

Operation altitude: 10000ft
Aircraft speed: 500km/h (Mach 0.42)
Inlet stagnation pressure: 69692.206 Pa
Inlet stagnation temperature: 268.35 K
Inlet density: 0.905kg/m^3

First I started by the following design steps:
Compressor> Diffuser> Combustor>Turbine stator>Turbine>Exhaust and finally compressor inlet (which is a bit complicated to design due to tip clearance).

But clearly this order doesn't work. Simply because when I designed the compressor I didn't take time to solve combustion equations inside the combustor therefore I got an incorrect air mass flow rate inside the engine. The design steps look more like the following:

Combustion equations>Compressor>Turbine>Combustor>remaining steps

So I had to start again with a larger compressor . I wanted to share my work so /scibros can give a critical assessment of it and if possible provide some solutions of encountered problems. I will update this thread on a regular basis. Toodles