AN ANALYTICAL AND EXPERIMENTAL INVESTIGATION OF LAMINAR AND TURBULENT AIR FLOW IN A TUBE WITH AN ENTRANCE MACH NUMBER OF FIVE.
MASSACHUSETTS INST OF TECH CAMBRIDGE DEPT OF MECHANICAL ENGINEERING
Pagination or Media Count:
The use of the flow in the entrance region of a tube was demonstrated as being a practical and inexpensive means for obtaining accurate data for laminar boundary layer flows at supersonic and hypersonic speeds. The measurements for the laminar boundary layer, obtained with an entrance Mach number of about five, were in excellent agreenent with available theoretical predictions. Special features of the apparatus for the high-speed flow research program included a test section constructed with removable sections, a micromanometer for use at low pressures and with improved response characteristics, and small combination probes for boundary layer studies. An investigation was made of the adiabatic flow of air in the entrance region of a tube with an inlet Mach number of about five. The measured static pressures, wall temperatures, recovery factors, local friction coefficients, boundary layer profiles, etc. were in excellent agreement with available theoretical predictions for the laminar boundary layer. The results for the turbulent boundary layer and location of transition were in good agreement with available data.