Abstract The aerodynamics of re-entry vehicles has always been in the forefront among space research. With the increasing interests in space exploration, it is important to understand the aerodynamics of spacecrafts and identify an optimum design to overcome the forces due to the earth's atmosphere. In this paper, Computational Fluid Dynamic (CFD) analysis has been carried out on ballistic bodies with a single, double and triple aero-disk spikes. The study also involves the presence and absence of a blunt tip to aid the analysis of flow behaviour on these bodies under two scenarios namely zero-degree angle of attack and at supersonic speed (Mach 2.0). The aerodynamic drag and surface heat transfer effects of these spikes on three different blunt body configurations has been studied. The shape of the blunt bodies vary based on the nose bluntness factor. The flow patterns of these configurations were three-dimensionally visualized via Schlieren-like, Mach and Pressure contours. It was observed that the usage of aero-disk spike reduced the aerodynamic drag by 45%–60% when compared to the bodies without spikes. The configuration labelled 3221 showed the maximum effect with an average drag reduction of more than 55%. There was a remarkable drop in the stagnation point value of surface heat flux with the addition of all five spike system. An efficient performance of localized peak heat fluxes was also noticed upon the addition of double and triple spike systems. In conclusion, it has been observed that the usage of double and triple spikes on the 3221 blunt body has significantly improved its aerodynamic drag and its surface heat flux.

    Highlights Supersonic Flow over Multiple Aero Disk spiked Ballistic bodies varying on the nose bluntness factor. Comparison of Drag and Surface heat flux values of the Multiple spiked configurations. Double and Triple Aero Disk Spikes Perform better in terms of Aerodynamic Drag and Heat Flux reductions. Schlieren images, Mach and Temperature contours are plotted to understand the flow behaviour.


    Zugriff

    Zugriff prüfen

    Verfügbarkeit in meiner Bibliothek prüfen

    Bestellung bei Subito €


    Exportieren, teilen und zitieren



    Titel :

    Thermo-Fluid Analysis of Supersonic Flow Over Ballistic Shaped Bodies with multiple aero-disk spike configurations


    Beteiligte:

    Erschienen in:

    Acta Astronautica ; 180 ; 292-304


    Erscheinungsdatum :

    2020-12-13


    Format / Umfang :

    13 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch




    Aero-spike and aero-disk effects of on wave drag reduction of supersonic flow past over blunt body

    Balusamy, Kathiravan / A., Vinothraj / V., Suresh | Emerald Group Publishing | 2024



    Hypersonic Flow over Ballistic Reentry Configurations

    Patil, M.M. | Online Contents | 1999



    Spike-Nosed Bodies and Forward Injected Jets in Supersonic Flow

    Gilinsky, Mikhail / Washington, Christopher / Blankson, Isaiah et al. | AIAA | 2002