CFD Analysis Of Delta Wing Body Configurations At Lower Angle Of Attack

The delta wing is a wing plan form in the form of a triangle. It is named for its similarity in shape to the Greek letter delta (Δ). The first practical uses of delta wing came in the form of so-called "tailless delta", i.e. without the horizontal tail plane. As the angle of attack increases, the leading edge of the wing generates a vortex which energizes the flow, giving the delta a very high stall angle.Pure delta-wings fell out of favour somewhat due to their undesirable characteristics, notably flow separation at high angles of attack, high drag at low altitudes, low wing loading and poor maneuverability. The design of modern light weight fighter that can cruise supersonically, maneuver transonically and has a post stall capability requires additional highly swept area ahead of the main wing called strake or leading edge extension (LEX) which lead to some of the variations in delta wing such as tailed delta, cropped delta, double delta, cranked arrow and ogival delta. The present project work investigates the flow field over a typical cropped delta and double deltawing body configuration at low angles of attack (α) from 0 to 15 degrees with an increment of step 3. Delta wing with sweep angle of 60 degrees and double delta wing with a sweep of 55/60 degrees having a beveled leading edge are modeled and simulated at Mach number 0.4 and at a Reynolds number (Re) of 2.7x104]. The flow simulations are carried out by the unstructured hybrid meshes comprising of tetrahedral and prism elements created by ICEMCFD. The meshes are refined adequately to resolve the boundary layer flow. The flow simulations are carried out by ANSYS FLUENT. The aerodynamic characteristics of both the wing body configurations are compared to find which is to be more effective. The computed data obtained is also compared with the available experimental data.