Abstract
The effect of nonequilibrium air chemistry on skin friction and Stanton number and the applicability of the reference temperature method and Reynold's analogy for such conditions was investigated. The nonequilibrium laminar boundary layer equations were solved on a flat plate geometry for different Mach numbers, altitudes and wall to edge temperature ratios. A correlation of a modification to the reference temperature method is made for application in the presence of nonequilibrium dissociated air at hypersonic speeds. 17 refs.
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.
