Abstract
A hypersonic e ight experiment was conducted for development of the Japanese unmanned operational orbiting plane. The following aerodynamic characteristic data are presented for a e ight ranging in Mach number from 2 to 14: aerodynamic force coefe cients, longitudinal trim characteristics, stability and control derivatives, elevon hingemoment, and surfacepressuredistribution.Thedata arecomparedwithpree ightpredictionsbased on windtunnel test results and computational e uid dynamiccalculations to evaluate the validity of the prediction methods, including determination of uncertainty in the vehicle design. The prediction methods are proven to be generally valid for design of lifting re-entry vehicles at a high angle of attack, whereas some anomalies are found in axial force, elevon trim angle, and reaction-control-system gas-jet interaction.
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.
