Chakrabarthy, SK and Dhanalakshmi, K and Mathur, JS (1998) Euler Analysis of SARAS Wing-fuselage Configuration. Technical Report. National Aerospace Laboratories, Bangalore, India.
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Abstract
The design and development of a 9--14 seater Light Transport Aircraft (LTA), named SARAS, has been taken up at NAL recently. Reliable aerodynamic data is urgently13; required for this configuration, in order to freeze the design. A vertex based Euler code, JUEL3D, has been employed to compute inviscid flow past the SARAS wing-fuselage configuration. The algorithm uses a vertex based finite volume space discretization with a five stage Runge-Kutta time stepping scheme. Enthalpy damping, implicit residual smoothing, local time stepping and grid sequencing are used to accelerate the convergence to steady state. A blended second and fourth order artificial dissipation is also used for stability. The code is multi-block structured and can handle any arbitrary13; single/multi-body geometry. Computations have been carried out on a multi-block grid generated by the grid generation code, JUMGRID, which uses a hybrid algebraic/elliptic13; method to generate a structured grid in a particular block (whereas the blocks may be unstructured) and can be used for any arbitrary, geometrically complex body. Computed13; results are presented for subsonic flow at various angles of incidence and are compared with available experimental data.
| Item Type: | Proj.Doc/Technical Report (Technical Report) |
|---|---|
| Uncontrolled Keywords: | Euler equations;SARAS;Wing-Fuselage;Multiblock |
| 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: | Smt Bhagya Rekha KA |
| Date Deposited: | 16 May 2006 |
| Last Modified: | 24 May 2010 09:41 |
| URI: | http://nal-ir.nal.res.in/id/eprint/1430 |
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