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ID: 149008

Aerodynamic characterisation of ramjet missile through combined external-internal computational fluid dynamics simulation / Bhandarkar, Anand ; Chakraborty, Debasis ; Manna, P ; Basu, Souraseni

Chakraborty, Debasis	Journal Article
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Summary/Abstract

Combined external-internal flow simulation is required for the estimation of aerodynamic forces and moments of high speed air-breathing vehicle design. A wingless, X-tail configuration with asymmetrically placed rectangular air intake is numerically explored for which experimental data is available for different angles of attack. The asymmetrically placed air intakes and protrusions make the flow field highly three-dimensional and existing empirical relations are inadequate for preliminary design. Three dimensional Navier Stokes equations along with SST-kω turbulence model were solved with a commercial CFD solver to analyse the combined external and internal flow field of the configuration at different angles of attack. Estimated aerodynamic coefficients match well with experimental data and estimated drag coefficient are within 8.5 per cent of experimental data. Intake performance parameters were also evaluated for different angles of attack.

Key Words

Computational Fluid Dynamics ; CFD ; Ramjet ; Drag Coefficient ; Pressure Recovery ; Mass Capture Ratio

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ID: 130770

Numerical exploration of solid rocket motor blast tube flow fie / Javed, Afroz; Sinha, P K; Chakraborty, Debasis

Javed, Afroz	Journal Article
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2013.

Summary/Abstract

The blast tube flowfield of a solid rocket motor is explored numerically by solving 3-D RANS equations with SST Turbulence model using a commercial computational fluid dynamics (CFD) software CFX-10. Parametric studies are carried out to find out the effect of the blast tube diameter on the total pressure loss in the rocket motor. It is observed that the total pressure loss in the rocket motor is less than 4 per cent and the blast tube is contributing less than 1 per cent. It is also found out that higher the blast tube diameter, the lesser the drop in the total pressure. Blast tube geometry is not found to contribute significantly in the overall thrust and specific impulse in the rocket motor.

Key Words

Blast Tube ; Total Pressure Loss ; Computational Fluid Dynamics

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ID: 138624

Slag prediction in submerged rocket nozzle through two-phase CFD simulations / Chaturvedi, Amit Kumar; Kumar, Sudarshan ; Chakraborty, Debasis

Kumar, Sudarshan	Article
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Summary/Abstract

A computational procedure has been established to predict the slag in a practical solid rocket motor with submerged nozzle. Both single-phase and two-phase flow analyses have been performed in the rocket motor port. Three-dimensional Navier-Stokes equations along with SST turbulence model have been solved for gas-phase calculations. The effect of ejected alumina particles from the propellant geometry on the flow field has been simulated through Lagrangian tracking method. The computational methodology is firstly validated by comparing against other numerical results of rocket motors available in the literature before applying the same to predict the slag accumulation of a submerged rocket motor for strategic applications. Burn-back geometries at different instants have been simulated and parametric studies were performed to find out the effect of Al2O3 particle size. It was observed that the slag capture rate increases uniformly with A12O3 particle size. The predicted slag accumulation data match closely with the ground test data for the range of conditions simulated in the present work.

Key Words

Slag Prediction ; Submerged Rocket Nozzle ; CFD Simulation ; Solid Rocket Motor ; Rocket Motor Performance ; Nozzle Erosion

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