The pressure distribution on the nozzle wall near the exit cross section was studied experimentally for different incalculability factors.
Damping lengths
and internal pressure profiles in response to increases in the pressure drop across the shock discontinuity were determined up to a value close to the detachment value, for Mach numbers M=2 to 3.5.
Translated from Inzhenerno-Fizicheskii Zhurnal, Vol. 18, No. 2, pp. 233–236, February, 1970.