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Flight experiments on NASA Langley Research Center's B737-100 airplane were conducted to document ow characteristics for further understanding of the ow physics on multielement high-lift systems. The measurements presented in this paper show that signi cant regions of laminar ow exist on the main element and the fore ap of the airplane. Flow mechanisms that affect the extent of laminar ow include relaminarization of the ow in the leading-edge region of the main element and contamination of the laminar ow on the ap by turbulent shear layers emanating from upstream elements. This information should be valuable in the development and assessment of high-Reynolds-number wind-tunnel experiments and numerical models for predicting the ows around multielement wings at full-scale high-lift conditions. Nomenclature C p = pressure coef cient, ( p 2 p`)/qC p,max = maximum pressure coef cient in leading-edge region of main element c = local chord length, ft c = mean aerodynamic chord, 11.20 ft h p = pressure altitude, ft K = relaminarization parameter M`= freestream Mach number p = local static pressure, psf p`= freestream static pressure, psf q`= freestream dynamic pressure, psf R bar = attachment-line Reynolds number Rc = Reynolds number, V`c/n s = surface distance, ft t = time, s V i = indicated airspeed, kn Presented as Paper 95-3911 at

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