| dc.contributor.advisor | Holla, V S | |
| dc.contributor.advisor | Kamath, Hemanth | |
| dc.contributor.author | Srinivasa Murthy, P | |
| dc.date.accessioned | 2006-07-21T08:58:19Z | |
| dc.date.accessioned | 2018-07-31T05:15:00Z | |
| dc.date.available | 2006-07-21T08:58:19Z | |
| dc.date.available | 2018-07-31T05:15:00Z | |
| dc.date.issued | 2006-07-21T08:58:19Z | |
| dc.date.submitted | 2000 | |
| dc.identifier.uri | https://etd.iisc.ac.in/handle/2005/229 | |
| dc.identifier.srno | null | |
| dc.description.abstract | In this thesis we describe the development of Reynolds- averaged Navier Stokes code for the flow past two- dimensional configuration. Particularly, emphasis has been laid on the study of low Reynolds number airfoil aerodynamics.
The thesis consists of five chapters covering the back ground history, problem formulation, method of solution and discussion of the results and conclusion.
Chapter I deals with a detailed background history of low Reynolds number aerodynamics, problem associated with it, state of the art, its importance in practical applications in aircraft industries.
Chapter II describes the mathematical model of the flow physics and various levels of approximations. Also it gives an account of complexity of the equations at low Reynolds number regarding flow separation, transition and reattachment.
Chapter III describes method of solution, numerical algorithm developed, description of various upwind schemes, grid system, finite volume discrieti-zation of the governing equations described in Chapter II.
Chapter IV describes the application of the newly developed Navier Stokes code for the test cases from GAMM Workshop proceedings. Also it describes validation of the code for Euler solutions, Blasius solution for the flow past flat plate and compressible Navier Stokes solution for the flow past NACA 0012 Airfoil at low Reynolds number.
Chapter V describes the application of the Navier Stokes code for the more test cases of current practical interest . In this chapter laminar separation bubble characteristics are investigated in detail regarding formation, growth and shedding in an unsteady environment.
Finally the conclusion is drawn regarding the robustness of the newly developed code in predicting the airfoil aerodynamic characteristics at low Reynolds number both in steady and unsteady environment.
Lastly, suggestion for future work has been highlighted. | en |
| dc.format.extent | 5610350 bytes | |
| dc.format.mimetype | application/pdf | |
| dc.language.iso | en | |
| dc.publisher | Indian Institute of Science | en |
| dc.rights | I grant Indian Institute of Science the right to archive and to make available my thesis or dissertation in whole or in part in all forms of media, now hereafter known. I retain all proprietary rights, such as patent rights. I also retain the right to use in future works (such as articles or books) all or part of this thesis or dissertation. | en |
| dc.subject.classification | Aeronautics | en |
| dc.subject.keyword | Airfoils - Aerodynamics | en |
| dc.subject.keyword | Reynolds number | en |
| dc.subject.keyword | Navier Stokes Code | en |
| dc.subject.keyword | Flow Physics | en |
| dc.subject.keyword | Viscous Flow | en |
| dc.subject.keyword | Grid Generation | en |
| dc.subject.keyword | Reynolds Averaged Navier Stokes (RANS) Solution | en |
| dc.subject.keyword | Euler Solution | en |
| dc.subject.keyword | Baldwin-Lomax Turbulence Model | en |
| dc.title | Low Reynolds Number Airfoil Aerodynamics | en |
| dc.type | Electronic Thesis and Dissertation | en |
| dc.degree.name | PhD | en |
| dc.degree.level | Doctoral | en |
| dc.degree.grantor | Indian Institute of Science | en |
| dc.degree.discipline | Faculty of Engineering | en |
