By Holt Ashley
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Extra info for Aerodynamics of Wings and Bodies
Because of the momentum loss due to the turbulent mixing in the wake the drag of the body will be quite large. On a thin airfoil at a small angle of attack the boundary layer will separate at the sharp trailing edge but there will be a very small wake so that a good model for the flow is the attached flow with the Kutta condition for the inviscid outer flow determining the circulation. 4-3 Boundary Layer on a Flat Plate We shall consider the viscous laminar high Reynolds number flow over a semi-infinite flat plate at zero angle of attack.
01, one would expect good agreement between the first-order theory and experiments. As seen from Fig. 4-3 this is indeed the case; the experimental points are almost indistinguishable from the theoretical curve. The Blasius solution just described was the first successful attempt to solve Prandtl's more general boundary layer equations. 0 FIG. 4-3. Velocity distribution in a Oat-plate boundary layer. [Adapted from Boundary Layer Theory by H. Schlichting, Copyright @ (1960) McGraw-Hili Book Company.
Define the distribution of thickness and camber, respectively, along the chord. If will be assumed that 71 and Ti are both smooth and that U' and Ti' are of order of unity everywhere along the chord. A blunt leading edge is thus excluded. In the limit of E -+ 0 the airfoil collapses to a segment along the x-axis assumed to be located between x = 0 and x = c. We will seek the leading terms in a series expansion in E of cI> to be used as an approximation for thin airfoils with small camber and angle of attack.