Aerodynamic Performance Enhancement of Supersonic 2D Missile Using ANSYS

Aerodynamic Performance Enhancement of a NACA 66-206 Airfoil Using Supersonic Channel Airfoil Design

Supersonic channel airfoil design techniques have been shown to significantly reduce drag in high-speed flows over diamond shaped airfoils by Ruffin and colleagues. The effect of applying these techniques to a NACA 66-206 airfoil is presented. The design domain entails channel heights of 8-16.6% thickness-to-chord and speeds from Mach 1.5-3.0. Numerical simulations show an increase in the lift-...

High-Performance Supersonic Missile Inlet Design Using Automated Optimization

A multi-level design strategy for supersonic missile inlet design is developed. The multi-level design strategy combines an e cient simple physical model analysis tool and a sophisticated CFD Navier-Stokes analysis tool. The e cient simple analysis tool is incorporated into the optimization loop and the sophisticated CFD analysis tool is used to verify, select and lter the nal design. The Genet...

High Performance Supersonic Missile Inlet Design Using Automated Optimization

Effects of Some Geometric Variations on Missile Aerodynamic Characteristics at Supersonic Speeds

Multiobjective Aerodynamic Optimization of Supersonic Wings Using Navier-Stokes Equations

The design optimization of a wing for supersonic transport by means of Multiobjective Genetic Algorithm (MOGA) is presented. The objective function is to minimize the drag for transonic cruise, the drag for supersonic cruise and the bending moment at the wing root for the supersonic condition. The wing shape is defined by planform, thickness distributions and warp shapes, in total of 66 design ...