Pressure distribution over blunt body in supersonic annular jet stream

We present the experimental results of the investigation of pressure distribution over a blunt-nosed cylindrical body placed in the annular jet which flows out of the nozzle of the first body of revolution. The investigation was carried out at the effective Mach number M-j approximate to 1,24 at the nozzle exit. It was shown that the nondimensional surface pressure at each measured point on the blunt-nosed body p was practically invariable at the values of the ratio of stagnation pressure in the nozzle plenum chamber to atmospheric pressure N = p(oj)/p(alpha) = 1,637...4,143.