Subramanian, NR and Chakrabartty, SK (1985) Transonic flow computations around finite wings. Technical Report. National Aeronautical Laboratory, Bangalore, India.
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Abstract
Three dimensional transonic flow computations are extremely complex due to the nonlinearity in the equations as well as the excessive computer storage requirements.13; Two computer programmes-STWING and SFL022 (adapted versions of HASA and Jameson's codes respectively,) have been made operational on the UNIVAC 1160/H1 computer at NAL. The SWING solves the full conservative 3D transonic potential equation for a wing in the conservative form using the approximation factorization scheme. The SFL022 solves the non-conservative form of the 'Gransonic full potential equation using a relaxation scheme. These programmes have been applied to a , typical ONERA M6 wing. Comparisons between STWING and SFL022 for the same configuration (ONBRA M6 Wing) have been made with calibrated experimental results. It is observed that both the codes predict the pressure distribution and shock waves satisfactorily. The STWING predicts better the double shock structure typical of such wings, the shock wave and pressure distribution.
| Item Type: | Proj.Doc/Technical Report (Technical Report) |
|---|---|
| Uncontrolled Keywords: | Compressible flow;Transonics;Aerodynamics CFD |
| Subjects: | ENGINEERING > Fluid Mechanics and Thermodynamics |
| Division/Department: | Fluid Dynamics, Fluid Dynamics |
| Depositing User: | Deputy Head Poornima Narayana |
| Date Deposited: | 24 Aug 2006 |
| Last Modified: | 24 May 2010 09:46 |
| URI: | http://nal-ir.nal.res.in/id/eprint/2212 |
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