Design Optimization and Analysis for A Vertical Flight Technique (Aerodynamic Analysis)

Abstract

This report is about designing new parts that enable the fighters to perform the vertical flight maneuver depending on the fixed wing lift, with minimum fuel consumption and suitable layout for super maneuverability aircrafts (applied at sukhoi-35). In order to perform this maneuver with minimum fuel consumption and keep suitable layout we had conceptually designed new parts (sliding parts) that kept inside the wing structure and then extent along the semi span, the sliding parts work as storage for the fans. The fans are small diameter fans distributed equally along the semi span stored inside the sliding parts, it’s function is to accelerate the flow over the wing thus increasing the wing lift. All mathematical models of sukoi-35 had been built using calculation and Microsoft office excel 2016, starting with aerodynamic model using thin airfoil theory and aerodynamics all aerodynamic parameters had been calculated, stability model had been estimated and also the structural model. Conceptual design of the sliding parts and fans had been done starting with sizing satisfying the requirements, and both of them had been drown using CATIA v5, then they had been incorporated into the original CAD model of sukhoi-35. Finally, computational aerodynamic analysis had been done using CFD (fluent), and all results had been discussed.