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So I can't exactly find out what angle should the converging part of the rocket chamber be or why different angles are chosen for engines (varies by about 15°).

Are there any guidlines on the angle or equations?

Thanks!

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Have a look at Sutton (7th edition online here) Chapter 3.4

The converging nozzle section between the chamber and the nozzle throat has never been critical in achieving high performance. The subsonic flow in this section can easily be turned at very low pressure drop and any radius, cone angle, wall contour curve, or nozzle inlet shape is satisfactory.

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  • $\begingroup$ Ok so it doesn't matter. Have read this part, just had to varify. Thank you $\endgroup$ Commented Jan 5, 2021 at 21:08
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    $\begingroup$ Later in the Real Nozzles chapter 3.5 there is some discussion about not making it too short, but it seems that even that is not too important. $\endgroup$ Commented Jan 5, 2021 at 21:09

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