Altseimer, John H. (1948) An experimental investigation of detached shock waves. Engineer's thesis, California Institute of Technology. http://resolver.caltech.edu/CaltechETD:etd-12232008-153257
Using the Galcit 2 1/2 inch Supersonic Tunnel equipment, surface pressure measurements were taken on cylindrical models with cone-shaped noses. The total included angle of the cones was 75°. The Mach number range covered was from 1.41 to 1.99 which for 75° cones covers most of the range from detached to attached shock waves. Stagnation pressure measurements were also taken by means of blunt cylindrical models. Schlieren pictures were taken of the 75° cones and blunt models throughout the velocity range. Additional pictures of shock waves 45°, 60°, and 90° cones at some of the velocities used were also obtained. From the Schlieren pictures the traces of the shock waves were obtained and plotted on graph paper. Shock wave angles vs. distance from the model centerlines are also presented as well as the distribution of "M[subscript 2]", the Mach number directly behind the wave. Appendix #1 shows "Blocking" data for the 2 1/2 inch Galcit Tunnel. Hand adjusted flexible nozzle walls were used for most of the work. Satisfactory flow through the tunnel was obtained with these nozzle blocks. However, design improvements are possible and Appendix #2 recapitulates the problems encountered and offers suggestions for future use.
|Item Type:||Thesis (Engineer's thesis)|
|Subject Keywords:||Aeronautical Engineering|
|Degree Grantor:||California Institute of Technology|
|Division:||Engineering and Applied Science|
|Thesis Availability:||Public (worldwide access)|
|Defense Date:||1 January 1948|
|Default Usage Policy:||No commercial reproduction, distribution, display or performance rights in this work are provided.|
|Deposited By:||Imported from ETD-db|
|Deposited On:||15 Jan 2009|
|Last Modified:||28 Jan 2017 00:33|
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