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The design and operational characteristics of a new test leg for the High Reynolds Number Facility at Ames Research Center are presented, and the unique features of a test section for obtaining two-dimensional airfoil data are reviewed/The new facility operates at unit Reynolds numbers in the range of (1-30) X 10 6 /ft. Boundarylayer suction panels are used in the test section (16 in. wide by 24 in. high) to minimize sidewall interference effects. Flexible, easily adjustable upper and lower walls allow test-channel area-ruling so as to nullify Mach number changes induced by mass removal, to correct for longitudinal boundary-layer growth, and to provide contouring compatible with the streamlines of the model in free air.-section height in = mass-flow rate M = Mach number p = static pressure p t = pitot pressure p T = total pressure q = dynamic pressure Re = Reynolds number Re coo = Reynolds number based on airfoil chord length and freestream conditions T = temperature u, U = velocity x = stream wise coordinate measured from airfoil leading edge X = tunnel longitudinal station (see Fig. 5) y = distance from wall Z = upper or lower wall coordinate (see Fig. 5) a = angle of attack A ( ) = incremental quantity <5 = boundary-layer thickness 6* = boundary-layer displacement thickness <50 = displacement thickness with zero mass removal X 7 , X 2 . = test section width and height parameters, respectively < ( ) > = rms value Subscripts c = airfoil chord e = edge of boundary layer N = nominal value T = tunnel or total value TS = test section w =wall oo = freestream conditions 1,2 = boundary layer removal systems 1 and 2 (see Fig. 5)

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