Ja. Edwards et Lc. Squire, AN EXPERIMENTAL-STUDY OF THE INTERACTION OF AN UNSTEADY SHOCK WITH A TURBULENT BOUNDARY-LAYER AT MACH NUMBERS OF 1.3-AND-1.5, Zeitschrift fur Flugwissenschaften und Weltraumforschung, 18(4), 1994, pp. 253-264
In this paper the results are given of an experimental investigation i
nto the flow development and the surface pressures in an unsteady shoc
k boundary interaction at Mach numbers of 1.3 and 1.5. The experimenta
l is one in which a naturally grown turbulent boundary layer on the tu
nnel is disturbed by a normal shock wave spanning the test section of
the tunnel. The shock wave is oscillated by a periodic pressure distur
bance in the tunnel diffuser far downstream of the interaction. Both i
nstantaneous (spatially averaged) and time averaged results for the su
rface pressures are presented. These results are used to study the flo
w development and phase changes through the interaction over a frequen
cy range from 34 to 167 Hz. This frequency range was chosen to cover t
he range of parameters likely to occur in conditions corresponding to
stall flutter in the compressor fans of large bypass engines.