AN EXPERIMENTAL INVESTIGATION OF THE SURFACE PRESSURE AND THE LAMINAR BOUNDARY LAYER ON A BLUNT FLAT PLATE IN HYPERSONIC FLOW. VOLUME 2. LAMINAR BOUNDARY LAYER PROFILE ON THE FLAT PLATE
Abstract
The laminar boundary layer on unswept, 1/2-inch thick, cylindrically- blunted flat plate was examined at Mach numbers of 7, 10, 12 and 14; at Reynolds numbers from 9000 to 21,300, based on the plate thickness; and at angles-of- attack of 0, 10 (compression) and 15 degrees (expansion). The layer was probed at three stations, S/D = 8, 16 and 22 using a pitot probe and a sonic-pneumatic total temperature probe. The tests were conducted in the 12-inch continuous hypersonic wind tunnel of the Ohio State University Aerodynamic Laboratory. The two probe outputs, together with the static pressure at the wall, were processed through an analogue computer and the results, i.e., Mach number, velocity, temperature, etc., are tabulated as functions of distance from the surface. Integrations were performed to obtain displacement and momentum thicknesses. Skin friction was also obtained, through the measurement of the velocity gradient at the wall. The results are presented in tabulated form, while typical data are plotted to illustrate the trends established by Mach number, Reynolds number and angle-of-attack.
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 01, 1963
- Accession Number
- AD0403351
Entities
People
- JaeDong Lee
- T. C. Nark
Organizations
- Ohio State University