Chakrabartty, SK and Dhanalakshmi, K and Mathur, S (1994) Euler Computation for a Multi-Body Launch Vehicle. Technical Report. National Aerospace Laboratories, Bangalore, India.
Full text available as:![[img]](http://nal-ir.nal.res.in/style/images/fileicons/application_pdf.png) | PDF Restricted to Archive staff only Download (3991Kb) |
Abstract
A vertex based Euler code, JUEL3D has been employed to compute supersonic flow past a multi-body launch vehicle. The code is multi-block structured and capable of handling any arbitrary three dimensional single/multi-body geometry. The algorithm is based on vertex based finite volume space discretisation with five stage Runge-Kutta time stepping scheme to advance the solution in time.13; Enthalpy damping, implicit residual averaging, local time stepping and grid sequencing are used to accelerate the convergence to steady state.13; The computations have been carried out on a stacked H type grid for13; III,, - 2.09 and a = 0 xB0;and 4 xB0; and the results are compared with13; experiments. Details of the Eider solver, and the grid generation codes13; are also explained in this report along with sample input/outout to13; introduce the code to general users.
| Item Type: | Proj.Doc/Technical Report (Technical Report) |
|---|---|
| Uncontrolled Keywords: | Euler equations;Launch vehicle;Multi-body |
| Subjects: | ENGINEERING > Fluid Mechanics and Thermodynamics |
| Division/Department: | Computational and Theoretical Fluid Dynamics Division, Computational and Theoretical Fluid Dynamics Division, Computational and Theoretical Fluid Dynamics Division |
| Depositing User: | Mr. N A |
| Date Deposited: | 13 Jun 2006 |
| Last Modified: | 24 May 2010 09:42 |
| URI: | http://nal-ir.nal.res.in/id/eprint/1541 |
Actions (login required)
| View Item |
