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SummaryA method which can be used for the design of blown or unblown wing sections is described in this paper. A brief description of a variety of theoretical methods for computation of different fluid flow phenomena encountered on high-lift wing systems is presented. The most significant type of viscous flow - a confluent boundary layer flow, which is present on the upper surface of the flap, the vane and the main component of a high-lift system – is described and its importance to the performance of high-lift systems is illustrated. Results of computation of pressure distribution, boundary-layer characteristic, and lift coefficient for two-dimensional high-lift systems are compared with experimental data in order to establish the validity and limitations of the method.

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Measurements of flow parameters for a two-dimensional turbulent wall jet are presented in a range of ratios of slot stream velocity to external stream velocity with pressure gradients, not previously investigated. These data are utilized for the calculations of wall shear and shear distribution by numerical methods. Relationships among the parameters are considered. Nomenclature= similarity function for velocity profile in the jet layer in initial region /fe) = similarity function for velocity profile in the wake layer in the initial region f(w) = similarity function for velocity profile in the jet layer in main region f(n±) = similarity function for velocity profile in the wake layer in the main region # = form factor or pressure gradient parameter H = ratio of dissipation energy thickness and momentum thickness M = Mach number PST = wall static pressure, lbf/ft 2 PT = Pitot tube total pressure, lbf/ft 2 Poo = freestream pressure lbf/ft 2 R e e = Reynolds number based on wall layer momentum thickness U c = velocity in the core layer in the initial region, fps U c (o) = slot velocity at the exit, fps U e (x) = velocity at the edge of viscous layer, fps U e (o) = velocity at the edge of viscous layer at the slot exit, f p s U w (x) = velocity at the junction of jet layer and wake layer, fps U m (x) = velocity at the junction of wall layer and jet layer, fps C/oo = freestream velocity, fps u = X component of velocity in viscous layer, fps v = Y component of velocity in viscous layer, fps

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