Modeling the excitation of shock waves in tubes by gaseous detonation

The emergence and development of a viscous, thermally conducting, compressible boundary layer behind a shock front in a tube is investigated numerically. The reverse effect of the boundary layer on the inviscid flow in the center of the tube is studied. It is shown that, in order to account for the effect of the tube walls on the external flow, nonstationary boundary layers must be computed, since averaging the losses over the transverse cross section of the tube may be too crude an approximation.