| TO STUDY A STEADY AND UNSTEADY CFD ANALYSIS OVER DELTA WING |
The study is aimed at assessing the application of the latest un stationary CFD method, detached Eddy simulation, to simulate the flow field around blunt leading edge delta wings.
For this purpose using different sweep back angle delta wing to perform numerical investigations at the Reynolds numbers of 6 million, Mach number of 0.4 and Angle of Attack of 18.5 to 24. As the nature of the study is mainly exploratory, various numerical grids have been used.
Viscous flow model will be used to realize the real flow physics. To study the behavior of the high-performance aircrafts featuring delta wing plan forms, in the past simplified geometry was the sharp leading edge, slender delta wing
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