抽象的

Estimation of Flow Field & Drag for Aerofoil Wing

Mahantesh. HM, Prof. Anand. SN

Investigation of airflow field over aerofoil wing is very essential to understand the flow complexity and its behaviour. In order to reduce the drag forces to achieve better performance with less power consumption for NACA 2415 model is been selected which is newly developed aerofoil wing. Drag force’s are very critical parameters to optimize the performance for various AOA’s. To understand flow complexity and how to reduce the fluid force parameters with the help of vortex generator kind of devices. Vortex Generators are highly efficient aerodynamic devices that are used widely in both external and internal aerodynamics as means of flow control. The paper deals with the CFD analysis of flow over wing at different flow regimes and as well different AOA’s without & VGs are placed on a wing. Complete three dimensional results are for the flow over wing equipped with Vortex Generators with various shapes and locations over the wing. The drag and lift characteristics of each shape and locations of VG’s have to be studied. The analyses has carried out for subsonic (M=0.5), transonic (M=1.0) and supersonic (M=2.0) flow regimes. The best shape and location of the VG’s for each of the flow regimes will be determined. All computations will be carried out using the RANS modelling which is available in commercially CFD package.