Abstract
At Japan Aerospace Exploration Agency, several Mars exploration missions have been proposed. In order to improve the feasibility of these Mars missions, aerodynamic characteristics have been investigated for flow regime from free-molecular to continuum. By carrying out a series of computations, such as free-molecular flow simulations, continuum flow simulations, and direct simulation Monte Carlo (DSMC) rarefied flow simulations, a bridging function method with DSMC parameters was found to represent the aerodynamic characteristics well. In transitional flow regime where Knudsen number is between 0.001 and 10, aerodynamic coefficients dramatically change. To keep the stability of an aeroshell in rarefied hypersonic flows, the range of its center of gravity location is more restricted for missions that use a blunt-body aeroshell.
Sign-in/Register to access full text options 
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.
