Publication Date:
2019-06-28
Description:
A system of nonlinear integral equations equivalent to the steady-state Krook kinetic equation was used to model the flow from a low-thrust axisymmetric nozzle. The mathematical model was used to numerically calculate the number density, temperature, and velocity of a simple gas as it expands into a near vacuum. With these quantities the gas pressure and flow directions of the gas near the exit plane were calculated and compared with experimental values for a low-thrust nozzle of the same geometry and mass flow rate.
Keywords:
SPACECRAFT PROPULSION AND POWER
Type:
NASA-CR-198934
,
NAS 1.26:198934
Format:
application/pdf
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