Shock Tube Flow Uniformity Experiments.
Abstract
A series of experiments was performed in the NASA Ames Electric Arc Shock Tube to investigate the uniformity of the shock heated flow field. The experiments were designed to record the flow field about cone and wedge probes. Shock angles were obtained from high speed, image converter framing camera images throughout the first 30 microsec of shock heated flow and used to determine the corresponding pitot pressure. The measured Mach angles all fall between 28 and 32 degrees; because of flow field distortion of the optical image, the measurement accuracy was plus or minus 2 degrees. For a static pressure of 2,200 psi, the pitot pressure corresponding to the measured Mach angle is 5,910 psi plus or minus 600 psi. Flow field distortion of the optical image may have been caused by recessed flat windows; additional experiments using flash windows are recommended. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Sep 23, 1979
- Accession Number
- ADA090349
Entities
People
- James E. Craig