Abstract
Under the experimental studies carried out to reduce the sonic boom intensity created by the aircraft by means of active action, the problem of measuring the shock wave parameters in nonuniform flow is considered. Comparison of the pressure profiles behind the shock wave obtained by means of a drained measuring plate and a comb of brake pressure probes is given. It is shown that the technique using brake pressure probes provides an acceptable reliability of pressure distributions measurements in the near zone of the model. The use of the drained plate leads to significant errors in measuring under nonuniform flow conditions. Analysis of the causes of signal distortion is carried out. The procedure for experimental data processing is presented.
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