Time-dependent simulation of reflected-shock/boundary layer interactionAn initial numerical/experimental investigation has been done to better understand multi-dimensional flow phenomena inside pulse facilities. Time-dependent quasi-one-dimensional and axisymmetric numerical simulations of complete shock tube flow are compared with experimental pressure traces recorded at the NASA Ames electric-arc driven shock tube facility (from cold driver shots). Of particular interest is the interaction between the reflected shock wave and the boundary layer. Evidence of the shock bifurcation caused by this interaction is clearly seen in the present experimental data. The axisymmetric simulations reproduce this phenomenon and demonstrate how this interaction can provide a mechanism for driver gas to contaminate the stagnation region. The simulations incorporate finite-rate chemistry, a moving mesh and laminar viscosity.
Document ID
19930039385
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Wilson, Gregory J. (Eloret Inst. Palo Alto, CA, United States)
Sharma, Surendra P. (NASA Ames Research Center Moffett Field, CA, United States)
Gillespie, Walter D. (Stanford Univ. CA, United States)
Date Acquired
August 16, 2013
Publication Date
January 1, 1993
Subject Category
Fluid Mechanics And Heat Transfer
Report/Patent Number
AIAA PAPER 93-0480
Meeting Information
Meeting: AIAA, Aerospace Sciences Meeting and Exhibit