The velocity gradient at the wall normal to the wall

[dat]

Homework Statement

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.

Homework Equations

Boundary layers

The Attempt at a Solution

 

[Chestermiller]

Homework Statement

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.

Homework Equations

Boundary layers

The Attempt at a Solution

View attachment 205740

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.

 

[scottdave]

@Chestermiller is right. Either your course should give a table to find the values, or a place to go find it. You might start with this one, though. http://www.engineeringtoolbox.com/air-absolute-kinematic-viscosity-d_601.html