Numerical Investigations of Aerodynamics Performance of Blunt Nose Cone with Aerodisk at Hypersonic Flow

The blunted nose cone with and without a sharp aerospike and an aerodisk of various diameters and lengths are investigated numerically in detail in the current study at a hypersonic Mach number of 10. The aerodisk diameter is described as d/D ratios such as 0.2, 0.4 and 0.6, and the length of the aerospike is represented as the L/D ratio of 1, 1.5 and 2. The main objective of the research is to examine the aerodynamic properties of blunt noses with and without aerodisks and aerospikes, as well as the influence of shock production over the model. The design of blunted nose cones with aerodisk was made up using CATIA and numerical investigation was performed on the ANSYS Fluent. The turbulence model of SST k-omega was considered for study. The current study revealed that shock patterns drastically varied nearer to the nose cone model at L/D ratio 2 and variation of drag reduction occurred due to the increase in d/D ratio and aerospike and also flow pattern over the model was clearly investigated.