First of all, we use remote-ignition fuses, which have a range of approximately 4 km and are entirely of our own design, to ignite our solid-fuel rocket. Right after the first ignition, the compressed air will come to the combustion chamber of our nozzle, which we have designed aerodynamically and will give an estimated 1500N thrust, where the compressed air will move towards the throat of the nozzle with a pressure of approximately 450 psi. In the throat part, the velocity of the fluid is Mach 1 and the outlet velocity is approximately 2.4 Mach. For now, we will do the static ignition test of our engine, which we have designed and analyzed in a computer environment, in a very short time, stay tuned.

Render from Visualize Connected.

Thanks my teammates @TN, @YT, @BD, @CE @HD ​​​​​​​@NK 

Edu ​​​​​​​3DEXPERIENCE  
TEKYAZ TEKYAZAkademi birbucukadana 

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