By John J. Bertin
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Extra resources for Aerodynamics for Engineers,
2. discussed at length in Chapter 4, the streamwise component of velocity is given by y 1>7 u = Uϱ a b d where d, the boundary-layer thickness at a given station, is a function of x. Is a horizontal line parallel to the plate and a distance ⌬ from the plate (where ⌬ is equal to d at the downstream station) a streamline? (See Fig. , there is no flow through the wall). Thus, when y = ⌬, v = ve = U ϱ ⌬ 8>7 dd a b 8 d dx Since v is not equal to zero, there is flow across the horizontal line which is ⌬ above the surface, and this line is not a streamline.
12a) has the various terms labeled for convenience: local acceleration, convection, body forces, pressure forces, and stress forces. Also notice that the viscosity m is considered to be dependent on the spatial coordinates. This is done since, for a compressible flow, the changes in velocity and pressure, together with the heat due to friction, bring about considerable temperature variations. 12) for example]. Finally, the units of the equation are force per unit volume, since we divided through by the volume during the derivation.
There is no flow through the wall). Thus, when y = ⌬, v = ve = U ϱ ⌬ 8>7 dd a b 8 d dx Since v is not equal to zero, there is flow across the horizontal line which is ⌬ above the surface, and this line is not a streamline. If the details of the flow are not of concern, the mass conservation principle can be applied directly to the entire region. 2) over a fixed finite volume in our fluid space (see Fig. 5) yields S 0r d(vol) + ٌ # (rV)d(vol) = 0 l l 0t vol vol 50 Chap. 5 Nomenclature for the integral form of the continuity equation.
Aerodynamics for Engineers, by John J. Bertin