Abstract
Using mixed momentum and energy integral equations, a simple quadrature method is developed to compute incompressible laminar boundary layer on a yawed infinite cylinder. As an illustration, the results — including various boundary layer thicknesses, form parameters and potential and surface streamlines — are obtained for a circular cylinder and compared with a known solution.
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Abbreviations
- I :
-
an integral of the mainstream velocity, eq. (9)
- K :
-
a shape parameter, eq. (8)
- q, r, s, t :
-
parameters, eqs. (6)
- R :
-
a reference length, radius of the circular cylinder
- u, v, w :
-
velocity components in the boundary layer
- U, V :
-
chordwise and spanwise components of mainstream velocity
- U ∞ :
-
a reference velocity, chordwise component of mainstream velocity in the undisturbed flow
- x, y, z :
-
coordinates
- α :
-
a parameter, eq. (17)
- δ 2x , δ 3x , δ 2y , δ 3y , δ 2xy , δ 3xy :
-
boundary layer thickness, eqs. (5)
- ν :
-
kinematic viscosity
- ε :
-
angle of deflexion, eq. (17)
References
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Sears, W. R., J. Aero. Sci. 15 (1948) 49.
Jones, R. T., N.A.C.A. T.N. No. 1402 (1947) and N.A.C.A. T.R. No. 884 (1949).
Wild, J. M., J. Aero. Sci. 16 (1949) 41.
Cooke, J. C., Proc. Camb. Phil. Soc. 46 (1950) 645.
Rott, N. and L. F. Crabtree, J. Aero. Sci. 19 (1952) 553.
Rosenhead, L. (Ed.), Laminar Boundary Layers, Oxford, 1966, p. 264 and 467.
Bhatia, J. C., J. Appl. Mech. 41 (1974) 557.
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Bhatia, J.C. Laminar boundary layer on a yawed infinite cylinder. Applied Scientific Research 30, 469–476 (1975). https://doi.org/10.1007/BF00455969
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DOI: https://doi.org/10.1007/BF00455969