AERODYNAMIC MODELING OF AN OGIVE NOSE PROJECTILE AT SUPERSONIC SPEED

Abstract

The aim of this thesis is to investigate the aerodynamics of an ogive nose projectile at supersonic speed. 2D Euler’s Equations is used to calculate the flow field around an ogive nose at Mach number 2. This algorithm uses MacCormack’s technique for discretization. The results of MacCormack’s technique are validated by 2D inviscid simulations of a commercial CFD code Fluent. There is a good agreement among results of both fore mentioned codes. Aerodynamic coefficients (lift and drag) are estimated using Potential and slender body theory at Mach number 1.2 to 2 and angle of attack of 2o to 10o . 3D simulations (Navier Stokes Equation) are done using Fluent. Pro‐Engineer Wildfire 3.0 is used for modeling the Ogive nose projectile. Gambit is used for preprocessing and meshing of projectile. TGrid scheme was used for meshing. Fine, medium and coarse mesh was generated and it was found that results are independent of mesh size. Spalart Allmaras model is used for turbulence modeling, which gives good results for aerodynamic applications. Aerodynamic coefficients (lift and drag) calculated using analytical theories and 3D CFD simulations show a good agreement.