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Theoretical investigation of frictional effects for laminar compressible flow in a tube entry

  • Tau-Yi Toong
  • Ascher H. Shapiro
Chapter

Summary

An approximate integral method is used for calculating the longitudinal pressure distribution of a laminar compressible flow in the entrance region of a duct. The method is based on the observation that when the boundary layer is thin, its growth along the duct is approximated by that for laminar flow over a flat plate. The velocity and temperature profiles in the boundary layer of the tube flow are assumed to be identical with those pertaining to a plate flow having a free-stream Mach number equal to the entrance Mach number of the corresponding tube flow.

This integral method has been used to compute the longitudinal pressure distribution, the mean pressure-gradient coefficient and the mean apparent friction factor for a laminar compressible flow in the entrance region of a round tube, for several entrance Mach numbers and thermal conditions at the wall.

In the case of constant values of specific heat, absolute viscosity and thermal conductivity of the compressible fluid, the computed approximate results are compared with those obtained by solving exactly the partial differential equations of motion. In the region where the integral method is considered to be valid, the agreement is within 5%, thus indicating the reliability of the procedure.

In the case of temperature-dependent viscosity and thermal conductivity, the computed results are compared with those obtained experimentally at Mach number 2.8, and the agreement is found to be within 8%.

For the incompressible case, the computed results are compared with those obtained by more exact integral methods and with experimental data. The agreement is good, except that at the limit of the region of validity of the present method, the discrepancy is increased to about 12%.

A plot is included showing, as a function of entrance Mach number, the ratio of the mean pressure-gradient coefficient for compressible flow to that for incompressible flow. With this information, the compressible-flow pressure distribution may be readily computed.

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Copyright information

© Springer Fachmedien Wiesbaden 1955

Authors and Affiliations

  • Tau-Yi Toong
    • 1
  • Ascher H. Shapiro
    • 1
  1. 1.Massachusetts Institute of TechnologyCambridgeUSA

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