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Introduction
Current institution
Publications
Publications (6)
The need to prevent and control rampant and
indiscriminate usage of energy in present-day realm on earth has
motivated active research efforts aimed at understanding of controlling
mechanisms leading to sustained energy. Although much has been
done but complexity of the problem has prevented a complete
understanding due to nonlinear interaction bet...
In flame spread research, an important area of concern is establishing operating criteria in presence of an external energy source. The work is motivated by the need to understand the flame behavior in presence of an external electric influence to produce unique combustion results that are not simple interpolations. Through systematic experimentati...
Transitional phenomena of smoldering combustion over thin solid fuels are investigated. An experimental setup was upraised and implications of both smoldering and flaming external heat sources are estimated. Incense sticks were used as potential fuel and external smoldering heat source along with a fixed candle flame. The role of key controlling pa...
The application of dimple like protrusions or depressions on wing planforms have been proven to be beneficial causing reduction in pressure drag and delaying boundary layer separation. The present work focuses on optimizing the placement of multiple dimples at the trailing edge of wings to keep boundary layer attached. Optimization in terms of size...
The corrosion of grids in ion thrusters due to unsymmetrical leaks and beam dissipation which tends to decrease lifetime of thruster. Usage of cathode neutralizers have shown to decrease corrosion and effect the thrust vector of main electron beam. The existing neutralizer configurations reduce backfiring rate of flow to a minimal level, which has...
Questions
Questions (4)
Need weight of each component and their dimensions, also mass and velocity data of any of ion bombardment thrusters ( otherwise any other thruster data too is welcome )?
how do i calculate the thrust of the rocket , its exit velocity and Specific impulse from just its mass flow rate? I have data about the gas i.e. xenon, and its mass flow rate at exit.
As we know about NEXT ion thruster developed by NASA and simulate thrusters by different organizations, they have a common design technique- a bombardment region which releases ions for thrust ( known as anode) and a sprayer system known as cathodic neutralizer. So how do I calculate mass flow rate from both of them ( mass output from them) to produce thrust or are their any specific calculations or specifications or values already present about previously developed ion thrusters mass flow rate ?
Which free available simulation software is there which could help simulate ion path after they are released from a source under action of magnetic and electric and other fields and depending on the angle they are released at?
