Micro-nozzle flow and thrust prediction with high-density ratio using DSMC selection limiter

Introduction: A Direct Simulation Monte Carlo (DSMC) solver with a modified collisional routine is used to investigate an argon gas flow through millimeter-scaled thruster nozzle high-density ratios. Method: The limiter scheme, denoted as the constant selection (CSL), limits possible number of selected pairs value in accordance present simulation particles cell. Results: Results CSL scheme are compared experimental and numerical results compressible Navier–Stokes discussed comparison baseline DSMC simulations. influence collision limitation by on stagnation pressure thrust specific impulse prediction. application makes prediction challenging some cases. Discussion: In contrast, predicted well, their study remains valid. Investigated mass rates 0.178 mg/s ≤ m . 71.360 mg/s, Knudsen numbers below Kn = 0.01 over 10 present. Near atmospheric conditions reached inside thruster, generating ratios up 3,741 along nozzle. computational performance also discussed, speed-up factors 0.51 achieved.