A forward facing step study: the step height less than the boundary-layer thickness /

An experimental investigation involving a thick, adiabatic, naturally turbulent, two-dimensional boundary layer undergoing separation has been completed at the Naval Ordnance Laboratory (NOL). Forward facing steps (with attached end plates) were used to induce boundary-layer separation for the particular case where the step heights, h, were less than the boundary-layer thickness, delta. The tests were conducted at a free-stream Mach number of 4.9 with a range of unit Reynolds numbers varying from 0.8 x 10 to the 6th power per foot to 4.0 x 10 to the 6th power per foot. The pressure distributions measured in the separated region ahead of the steps were found to be functions of both Re sub delta and h/delta for the turbulent boundary-layer separation case where h <delta."11 May 1973."Includes bibliographical references (pages 12-13)An experimental investigation involving a thick, adiabatic, naturally turbulent, two-dimensional boundary layer undergoing separation has been completed at the Naval Ordnance Laboratory (NOL). Forward facing steps (with attached end plates) were used to induce boundary-layer separation for the particular case where the step heights, h, were less than the boundary-layer thickness, delta. The tests were conducted at a free-stream Mach number of 4.9 with a range of unit Reynolds numbers varying from 0.8 x 10 to the 6th power per foot to 4.0 x 10 to the 6th power per foot. The pressure distributions measured in the separated region ahead of the steps were found to be functions of both Re sub delta and h/delta for the turbulent boundary-layer separation case where h <delta.Mode of access: Internet

The shock heights of static free jets /

The report describes the results of an experimental study involving a two-dimensional, underexpanded, free jet flowing into a static medium. The investigation was concerned with the determination of jet heights as a function of the nozzle flow properties. In support of this objective experimental results of two supersonic nozzles (Mach numbers of 2.89 and 2.99 and throat widths of 0.0335 inch and 0.0204 inch, respectively) are presented along with a complete data tabulation which includes photographs. A universal data correlation, expanded to include the axisymmetric jet case, is presented."11 January 1972."Includes bibliographical references (page 6)The report describes the results of an experimental study involving a two-dimensional, underexpanded, free jet flowing into a static medium. The investigation was concerned with the determination of jet heights as a function of the nozzle flow properties. In support of this objective experimental results of two supersonic nozzles (Mach numbers of 2.89 and 2.99 and throat widths of 0.0335 inch and 0.0204 inch, respectively) are presented along with a complete data tabulation which includes photographs. A universal data correlation, expanded to include the axisymmetric jet case, is presented.Mode of access: Internet