Accession Number : AD0428238


Title :   TURBULENT BOUNDARY LAYER CHARACTERISTICS, IN SUPERSONIC STREAMS HAVING ADVERSE PRESSURE GRADIENTS


Corporate Author : UNITED TECHNOLOGIES CORP HARTFORD CT


Personal Author(s) : McLafferty, George H ; Barber, Robert E


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/428238.pdf


Report Date : Sep 1959


Pagination or Media Count : 131


Abstract : investigations were conducted to determine the thickness and profile shape characteristics of turbulent boundary layers in supersonic streams having adverse pressure gradients similar to those which are encountered in supersonic inlets. The program included tests conducted at Mach numbers from 2.0 to 3.5 using two-dimensional and axisymmetric curved-surface models to produce the adverse pressure gradients. The magnitude of the gradients relative to the boundary layer thickness at the beginning of the gradient was varied by employing models having different radii of curvature and by changing the boundary layer thickness at the beginning of the gradient. The over-all pressure rise in most cases was greater than the value which would cause a turbulent boundary layer to separate if the pressure rise were created by an oblique shock wave. Some tests were conducted to determine the effect of boundary layer removal from the curved surfaces on boundary layer growth and on the pressure gradients which could be realized without separation. An analytical investigation was also conducted so that the results of the experimental investigation could be applied to the prediction of cases outside the range of the experiments.


Descriptors :   *DUCT INLETS , *TURBULENT BOUNDARY LAYER , CURVED PROFILES , JET MIXING FLOW , PRESSURE , SCHLIEREN PHOTOGRAPHY , SEPARATION , SHOCK WAVES , SUPERSONIC CHARACTERISTICS , SUPERSONIC FLOW , TURBOJET INLETS , WIND TUNNEL MODELS


Subject Categories : Pumps, Filters, Pipes, Tubing, Fittings & Vlvs


Distribution Statement : APPROVED FOR PUBLIC RELEASE