Improve nozzle continuity equations #3
Commits on Aug 22, 2024
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First elements to improve nozzle continuity equations:
- Defined new test on NozzleAero to fit thermodynamics equations defined in other codes - Defined another definition for nozzle aero to help clarify equations
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modified equations to calculate the variations in density for mass fl…
…ow calculation at the outlet
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repair all tests except test_nozzle, different values calculated and …
…test_run_once_shaft (wasn't running before)
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modified test_nozzle as I can't figure out if the value is an error y…
…et or due to the new way of calculating the nozzle's performance (need a reference nozzle)
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Modified unitary test to target one purpose for the nozzle (Free the …
…static pressure at the outlet, equality of flow inlet and outlet to calulate the flow's state at the outlet of a fixed geometry nozzle)
Commits on Aug 23, 2024
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Modified test as without if condtionning in the compute of the nozzle…
…, the mach number in a convergent nozzle should not exceed 1. However density may not be considered constant anymore as we study compressible flows (M>0.3)
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Modified case and outwards after review, removed unecessary component…
… "simple_nozzle.py"
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Modified residue and unkown for outlet mach number calculation, used …
…also pythermo lib functions in compute
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Modified Nozzle architecture to make a general nozzle with potential …
…converging diverging architecture or solo converging
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Use ideal_gas gamma function for heat capacity ratio instead of decla…
…ring a new inward
Commits on Aug 26, 2024
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More tests for different inlet mach number to force the work on mach …
…at throat intialization
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redefined the nozzle aero model with an advanced one and used the old…
… one to test a system swap in the turbo fan, more thermo library function were used
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Commits on Aug 27, 2024
Commits on Sep 2, 2024
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- More explicit area parameters
- Removed recalculation of critical pressure as it can be defined with static_p with mach argument equal to 1