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Modern View
COMPUTATIONAL FLUID DYNAMICS
(4)
answer(s).
Srl
Item
1
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
0 Rating(s) & 0 Review(s)
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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2
ID:
130770
Numerical exploration of solid rocket motor blast tube flow fie
/ Javed, Afroz; Sinha, P K; Chakraborty, Debasis
Javed, Afroz
Journal Article
0 Rating(s) & 0 Review(s)
Publication
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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3
ID:
139079
Numerical simulation of a hypersonic air intake
/ Saha , Soumyajit; Chakraborty , Debasis
Chakraborty , Debasis
Article
0 Rating(s) & 0 Review(s)
Summary/Abstract
Numerical simulations were carried out to study the unsteady flow in an intake of hypersonic air-breathing vehicle. Unsteady RANS simulations were performed to examine started flow of the intake when cowl surface is parallel to the ramp surface. Though started, the flow was unsteady due to flow separation bubbles inside intake. Intake with larger cowl opening at which intake unstarted was also simulated. Simulations indicated unstarted flow, with large pressure oscillations. The numerically simulation results match reasonably well with experimental data. Calculated unstarting Mach number was found to be 3.0-3.2 in comparison of wind tunnel data of 3.6 for the same cowl opening angle.
Key Words
Numerical Simulation
;
Computational Fluid Dynamics
;
Hypersonic Flow
;
Air Intake
;
Intake Unstarting
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4
ID:
141868
Shape optimisation of curved interconnecting ducts
/ Srinivasan, K; Balamurugan, V; Jayanti, S
Srinivasan, K
Article
0 Rating(s) & 0 Review(s)
Summary/Abstract
Practical ducting layout in process plants needs to satisfy a number of on-site constraints. The search for an optimal flow path around the obstructions is a multi-parameter problem and is computationally prohibitively expensive. In this study, authors proposed a rapid and efficient methodology for the optimal linkage of arbitrarily oriented fluid flow ducts using a single-parameter quadratic/cubic Bézier curves in two/three dimensions to describe the centreline of the curved duct. A smooth interconnecting duct can then be generated by extruding the duct face along the curve. By varying the parameter either along the angular bisector or along the axes of the ducts, a family of Bézier curves is generated. Computational fluid dynamics simulations show that the relationship between pressure drop and the adjustable parameter is a unimodal curve and the optimal connecting duct is the one which has the least pressure drop while satisfying on-site constraints can be used for linking the ducts. The efficacy of the method is demonstrated by applying it to some cases of practical interest.
Key Words
Computational Fluid Dynamics
;
Fluid Flow
;
Ducting
;
Shape Optimisation
;
Bézier Curves
;
Bernstein Polynomials
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