dc.contributor.authorImran Halimi Ibrahim
dc.date.accessioned2009-01-08T03:44:49Z
dc.date.accessioned2017-07-23T08:39:19Z
dc.date.available2009-01-08T03:44:49Z
dc.date.available2017-07-23T08:39:19Z
dc.date.copyright2008en_US
dc.date.issued2008
dc.identifier.citationImran, H. I. (2008). Fluid flow studies of the F-5E and F-16 inlet ducts. Master’s thesis, Nanyang Technological University, Singapore.
dc.identifier.urihttp://hdl.handle.net/10356/14581
dc.description.abstractThe intake represents the front of a complex aerodynamic system. The shape of the intake diffuser follows the contours of the aircraft for external aerodynamic reasons. However the meandering shape can result in unwanted secondary flow or swirl build up at the Aerodynamic Interface Plane (AIP), resulting in engine flutter and stall. Using the Finite Element Method (FEM) Partial Differential Equations (PDE) calculator COMSOL, the compressible flow equations were obtained by the coupling of the continuity and momentum equations in the k-ε turbulence model and the energy equation conduction and convections model. The standard validation and verification techniques employed in the computational analysis were conducted in the study of F-5E and F-16 aerodynamic intakes. The results were validated using experimental results of the circular S-duct. Static pressure contours of the S-duct were compared at the azimuthal angles 0ο, 90ο and 180ο with reasonable agreement. The Grid Convergence Index (GCI) study done on the circular S-duct, F-5E and F-16 intakes using the pressure recovery as variable.en_US
dc.format.extent155 p.en_US
dc.language.isoenen_US
dc.subjectDRNTU::Engineering::Aeronautical engineering::Jet propulsionen_US
dc.titleFluid flow studies of the F-5E and F-16 inlet ductsen_US
dc.typeThesisen_US
dc.contributor.schoolSchool of Mechanical and Aerospace Engineeringen_US
dc.contributor.supervisorNg Yin Kweeen_US
dc.description.degreeMASTER OF ENGINEERING (MAE)en_US


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