How to calculate the velocity gradient at the wall normal to the wall (Boundary layers)? 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.

I already know: $\tau_w = \mu\left(\frac{dV}{dy}\right)_{y=0} = 282$
but how to get $\mu$ ??

Also I don’t know what this is for: “The gas temperature at the wall is equal to standard sea level temperature”
In page 72 you'll find the value of µ at standard sea-level temperature...