Abstract
A space vehicle in atmosphere travels mostly at supersonic speed and generates a very strong bow shock wave around its blunt nose. This causes a large high-pressure area at the front nose surface accompanied with high temperature. It suggests high-pressure drag and high risk of heat shield failure. Oblique shock and conical separated flow zone generated by a forward disk-tip spike significantly reduce the drag by reducing the high-pressure area on the blunt nose. In the present work, aerodynamics of the high-speed spike-tipped blunt nose is investigated here numerically with Mach number up to 4.5. It is highlighted here that there exists an optimal combination of spike length and disk-tip diameter giving rise to minimal drag at supersonic speed. The reason for drag reduction is analyzed in detail.
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
