THE EFFECTS OF DRIVER TEMPERATURE GRADIENT ON SHOCK TUBE FLOW
Abstract
Shock tube initial condition is considered in which an axially distributed temperature gradient exists within the driver gas. Theoretical analysis of the wave interactions revealed that compression waves originating from the hotter regions of the driver gas overtake the shock wave and reinforce it progressively. A comparison is made of this case with the usual uniform-temperature driver case (zero gradient). A series of tests was conducted to correlate theory with experiment. The results qualitatively verified theoretical predictions that the compression waves reinforce the propagating shock wave. This phenomenon should minimize the effects of attenuation in shock tube flows. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Apr 25, 1962
- Accession Number
- AD0285537
Entities
People
- Lawrence Y. Lamb
Organizations
- The Aerospace Corporation