Accession Number:

AD0285537

Title:

THE EFFECTS OF DRIVER TEMPERATURE GRADIENT ON SHOCK TUBE FLOW

Descriptive Note:

Corporate Author:

AEROSPACE CORP EL SEGUNDO CALIF

Personal Author(s):

Report Date:

1962-04-25

Pagination or Media Count:

1.0

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

Subject Categories:

Distribution Statement:

APPROVED FOR PUBLIC RELEASE