Accession Number : ADA126919


Title :   An Experimental Study into the Scaling of an Unswept-Sharp-Fin-Generated Shock/Turbulent Boundary Layer Interaction.


Descriptive Note : Master's thesis,


Corporate Author : AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH


Personal Author(s) : McClure,William B


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/a126919.pdf


Report Date : Jan 1983


Pagination or Media Count : 123


Abstract : An experimental study was carried out of the three-dimensional shock wave/turbulent boundary layer flow-field generated by sharp fin with an unswept leading edge at a 10 deg angle-of-attack to the incoming flow. The model was mounted on and normal to either the tunnel floor or a horizontal flat plate. Both tests surfaces generated a fully developed, equillibrium tubulent boundary layer, with incoming thicknesses of 1.29 cm. and .45 cm., respectively. The incoming freestream was at a nominal Mach number of 2.95 and a Reynolds number of 6.3 x 10 to the 7th power/meter. All surfaces were near adiabatic wall temperature. The three objectives of this study were to learn more about the structure of this type of interaction, to examine the scaling of the resulting flow-field, and to obtain a detailed data set with which to compare numerical computations. The results show that the scaling of this type of interaction is dependent upon both local boundary layer thickness and freestream Reynold number.


Descriptors :   *SHOCK WAVES , *TURBULENT BOUNDARY LAYER , *THREE DIMENSIONAL FLOW , SCALE MODELS , INTERACTIONS , FLOW FIELDS , WIND TUNNEL TESTS , LEADING EDGES , FINS , WIND TUNNEL MODELS


Subject Categories : Fluid Mechanics


Distribution Statement : APPROVED FOR PUBLIC RELEASE