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ISSN Online: 2688-7231

ISBN Online: 978-1-56700-524-0

Proceedings of the 26thNational and 4th International ISHMT-ASTFE Heat and Mass Transfer Conference December 17-20, 2021, IIT Madras, Chennai-600036, Tamil Nadu, India
December, 17-20, 2021, IIT Madras, Chennai, India

Thermal effects on flow through micronozzles with various geometries

Get access (open in a dialog) DOI: 10.1615/IHMTC-2021.1700
pages 1121-1126


Cube satellite system requires secondary propulsion with micro nozzles for attitude control and minor corrections in the trajectory. In the current work, numerical simulation of 2D micro nozzles with different geometry and wall temperatures is studied. Steady state simulations through a finite volume simulation of 2D compressible Navier Stokes equations are carried out with the Maxwell firstorder slip condition at the wall when Knudsen number is higher than 0.001. Numerical analysis is carried out for various expansion angles, (5°, 15° and 30°), different wall temperatures (300K, 500K, 700K and 1000K) with constant inlet pressure. The thrust produced is observed to decrease with the expansion angle and wall temperatures. The nozzle with an expansion angle of 5° at a wall temperature of 300K shows the highest thrust in the currently studied range. The peak Mach number in the nozzle decreases with the wall temperature and increases with the expansion angle. Flow becomes rarefied as the wall temperature is increased. Subsonic layer thickness at the exit increases with expansion angle and wall temperature.