Thermo-Fluid Analysis of Supersonic Flow Over Ballistic Shaped Bodies with Multiple Aero- Disk Spike Configurations
Description
Computational Fluid Dynamic analysis has been carried out on Single, Double and Triple Aero-Disk Spiked Ballistic Shaped Bodies with and without blunt tip to understand the flow behavior on these structures at zero-degree angle of attack and at a Supersonic Speed of Mach 2.0. The aerodynamic drag and heat transfer effects of these spikes on three different blunt body configurations, whose shape vary on the Nose Bluntness factor is studied. The flow patterns on these configurations are three-dimensionally visualized through Schlieren and Mach contours. Through the simulations it is observed that the usage of aero disk spike has reduced the aerodynamic drag by about 45%–60% against the ones without spike in all the three cases and that the configuration labelled 3221 has been the best beneficiary due to this spike addition with an average drag reduction of more than 55% with all the five spike designs. There is a remarkable drop in the peak surface heat flux with the addition of all the five spikes systems. This drop in heat fluxes is significantly noticed with the addition of double and triple spike systems. Overall, it has been observed that the usage of double and triple spikes on the 3221 blunt body has been the best beneficiary in terms of aerodynamic drag and surface heat flux reduction. This Data Set consists of the conditions and the results files of the above research work. A sample problem setup file of the single spike case is added as well.These files can be viewed and opened in Hexagon | MSC Software, Cradle ScFlow v2020 and above. Apart from this, the results in the form of contours and graphs of the same is also available.