Abstract
An analytical methodology based on the Lees-Klineberg moment integral theory for two-dimensional, laminar, hypersonic viscous interaction has been developed to evaluate the aerodynamic control surface effectiveness of hypersonic winged vehicles, such as the Space Shuttle Orbiter, during high-angle-of-attack reentry. A quasi-three-di mensional approach, i.e., a strip analysis of the vehicle planform, is used. Computed incremental aerodynamic coefficients produced by flap/elevon deflections of the Space Shuttle Orbiter correlate very favorably with wind-tunnel test data. Qualitative control effectiveness trends due to the effects of wall cooling, Reynolds number, and finite control surface chord length are discussed.
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.
