Query Result Set
Skip Navigation Links
   ActiveUsers:2336Hits:21327168Skip Navigation Links
Show My Basket
Contact Us
IDSA Web Site
Ask Us
Today's News
HelpExpand Help
Advanced search
  Hide Options
Sort Order Items / Page
COMPUTATIONAL FLUID DYNAMICS (4) answer(s).
 
SrlItem
1
ID:   149008


Aerodynamic characterisation of ramjet missile through combined external-internal computational fluid dynamics simulation / Bhandarkar, Anand ; Chakraborty, Debasis ; Manna, P ; Basu, Souraseni   Journal Article
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.
        Export Export
2
ID:   130770


Numerical exploration of solid rocket motor blast tube flow fie / Javed, Afroz; Sinha, P K; Chakraborty, Debasis   Journal Article
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.
        Export Export
3
ID:   139079


Numerical simulation of a hypersonic air intake / Saha , Soumyajit; Chakraborty , Debasis   Article
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.
        Export Export
4
ID:   141868


Shape optimisation of curved interconnecting ducts / Srinivasan, K; Balamurugan, V; Jayanti, S   Article
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.
        Export Export