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The velocity gradient at the wall normal to the wall

  1. Jun 18, 2017 #1


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    1. The problem statement, all variables and given/known data
    This problem is from "Fundamentals of aerodynamics" by John D. Anderson, Jr (Fifth edition, page 101):
    Consider a flat plate at zero angle of attack in a hypersonic flow at Mach
    10 at standard sea level conditions. At a point 0.5 m downstream from the
    leading edge, the local shear stress at the wall is 282 N/m^2. The gas
    temperature at the wall is equal to standard sea level temperature. At this
    point, calculate the velocity gradient at the wall normal to the wall.
    2. Relevant equations
    Boundary layers
    3. The attempt at a solution
  2. jcsd
  3. Jun 19, 2017 #2
    viscosity of air is a function of temperature. In real life, we are not always given all the data needed to solve a problem, and we need to research some of the information, particularly values of physical properties.
  4. Jun 20, 2017 #3


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