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This paper reports results of experiments on the interaction of oblique shock waves with flat-plate boundary layers in the 30.48 X 30.48 cm (1x1 ft) supersonic wind tunnel at the NASA Lewis Research Center. These experiments were directed toward providing well-documented information of high accuracy useful as test cases for analytical and numerical calculations. Measurements of the plate surface static pressure and shear stress distributions as well as boundary-layer velocity profiles were obtained through the interaction region. Other measurements were also performed in order to document the tunnel test section flowfield and the two-dimensionality of the interaction regions. The findings presented provide detailed description of two-dimensional interactions with initially laminar boundary layers over the Mach number range 2.0-4.0. Additional information with regard to interactions involving initially transitional boundary layers was obtained at Mach numbers of 2.0 and 3.0 and those for initially turbulent boundary layers at Mach 2.0. Flow conditions encompassed a Reynolds number range of 4.72 X 10 6 -2.95 X 10 7 /m. These findings represent the most complete and detailed set of experimental information on oblique shock-wave/laminar boundary-layer interactions over the Mach number range 2.0-4.0. The data are available in digitized format for test case applications. Where comparison was possible, the shock /boundarylayer interaction results were found to be generally in good agreement with the experimental work of previous authors, both in terms of direct numerical comparison and in support of correlations establishing laminar separation characteristics. Nomenclature A,B,C, D, E, F = label to indicate axial location of velocity profile C' ^r w /Q n C f C FG L M N P P f Q R ratio of (rJ.Q^ at given to corresponding value at R x = 10 6 = length of separation pressure plateau = separation length based on distance between shear stress fit "zero" values = axial location of shock impingement = nominal tunnel dimension, defined to be 30.48 cm (12.000 in.) = Mach number = geographic direction: north = pressure = dynamic pressure = Reynolds number based on freestream conditions = unit Reynolds number based on freestream conditions U = axial component of mean flow velocity V = U/U e W = geographic direction: west x,y,z, X, 7, Z = coordinate dimensions X' = (x-x s )/XD XD = length of interaction region 0 ar Subscripts = shock generator angle with respect to plate == standard deviation = shear stress e = conditions in local freestream at axial location F = conditions at location at end of interaction G = conditions of Ref. 15 pi = plateau rise = ratio of pressures at end and start of interaction s = separation point st = stagnation conditions in plenum w = wall x = axial distance downstream from plate leading edge y = distance normal to plate surface oo = freestream conditions upstream of model 0 = conditions at start of interaction pressure rise Downloaded by UNIVERSITY OF OKLAHOMA on February 3, 2015 | http://arc.aiaa.org |

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