Abstract
An investigation was conducted in the Langley 8-Ft High Temperature Tunnel to obtain hypersonic pressure and heat-transfer data on a large scale (1/20) model of a hypersonic wing-body configuration. The model was tested at a nominal Mach number of 6; at two Reynolds numbers (0.6 and 1.6 x 106/ft); and at angles of attack from about 0 to about 15 deg. Results from this investigation indicate that both pressure and heat-transfer coefficients on the windward side of the configuration increased with increasing angle of attack; that leeside heattransfer coefficients remained relatively constant at slightly below the 0-deg level for all angles of attack; and that leeside pressure coefficients decreased slightly with increasing angle of attack but remained relatively close to a value of 0.
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.
