Abstract
A study was made of the shock tube boundary layer between the initial shock wave and the contact region for shock pressure ratios P21 of 2.75 and 8.0 with a corresponding Reynolds Number range of 0-50 X 10 and 0-100 X 10, respectively. The Reynolds Number is based on the distance behind the shock wave and fluid properties evaluated at the wall. Shadowgraph, schlieren, and interf erogram. photographs and thin-film thermometer measurements indicated that the region was almost completely occupied by turbulent boundary layer. Experimental density profiles and boundary-layer thickness measurements are presented together with calculated temperature and velocity profiles, displacement and momentum thicknesses, and local skin friction. Results are compared with the theory of Mirels in NACA T N 3712. In view of the assumptions of the theory the agreement is quite good. The velocity profiles at higher Reynolds Number for P21 = 2.75 follow a 1/5 power law closer than the 1/7 power law of T N 3712. For P2i = 8 all the experimental profiles are a 1/5 power. As a means of comparison the theory was redeveloped on the basis of the 1/5 power law for velocity.
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.
