Flowfield Measurements In A Slot Bled Oblique Shock Wave And Turbulent Boundary Layer Interaction Nasa Tm 1998 206974 Aug 6 1998 PDF Download

A shock-related separation of a turbulent boundary layer has been studied and documented. The flow was that of an axisymmetric turbulent boundary layer over a 5.02-cm-diam cylinder that was aligned with the wind tunnel axis. The boundary layer was compressed by a 30 deg half-angle conical flare, with the cone axis inclined at an angle alpha to the cylinder axis. Nominal test conditions were P sub tau equals 1.7 atm and M sub infinity equals 2.85. Measurements were confined to the upper-symmetry, phi equals 0 deg, plane. Data are presented for the cases of alpha equal to 0. 5. and 10 deg and include mean surface pressures, streamwise and normal mean velocities, kinematic turbulent stresses and kinetic energies, as well as reverse-flow intermittencies. All data are given in tabular form; pressures, streamwise velocities, turbulent shear stresses, and kinetic energies are also presented graphically. Brown, J. D. and Brown, J. L. and Kussoy, M. I. Ames Research Center SEPARATED FLOW; SHOCK WAVE INTERACTION; SHOCK WAVES; THREE DIMENSIONAL BOUNDARY LAYER; TURBULENT BOUNDARY LAYER; FLOW VELOCITY; GRAPHS (CHARTS); KINEMATICS; KINETIC ENERGY; PRESSURE; SHEAR STRESS; TABLES (DATA)...