Subramanian, NR and Chakrabartty, SK (1984) Computation of inviscid transonic flow past aerofoils using body fitted coordinates. Technical Report. National Aeronautical Laboratory, Bangalore, India.
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Abstract
Several numerical methods exist for solving two-dimensional transonic full potential equations, appear due to conservative or non-conservative forms of equations, satisfying boundary conditions on the surface of the body13; by extra polation or by using body fitted curvilinear coordinates obtained by different methods. Holst solved the conservative full potential equation fortransonic flow past arbitrary airfoil s and developed the TAD? code. The object of this work is to adapt the code to the existing computers (DZ 1090 and UNIVAC ll00/60HI) and try it out on various conventional and super critical airfoils Modifications are then introduced to improve the prediction of pressure distribution and shock position on13; super critical airfoils having extended regions of supersonic The differences flow , A suitable second order artificial viscosity term has been presented here and introduced in TAIR to get a second order accurate solution throughout the flow field except at the shock wave position , where it reverts to first order. The modified13; version of the code STAIR has been added are in the annexure.
| Item Type: | Proj.Doc/Technical Report (Technical Report) |
|---|---|
| Uncontrolled Keywords: | Inviscid transonic flow;Viscosity |
| Subjects: | ENGINEERING > Fluid Mechanics and Thermodynamics AERONAUTICS > Aerodynamics |
| Division/Department: | Flight Mechanics and Control Division, Flight Mechanics and Control Division |
| Depositing User: | M/S ICAST NAL |
| Date Deposited: | 14 Sep 2006 |
| Last Modified: | 24 May 2010 09:50 |
| URI: | http://nal-ir.nal.res.in/id/eprint/2727 |
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