Problem Description

To avoid doing hypersonic CFD of the entire rocket, we begin with the following assumptions:

• The fin is at 0 angle of attack
• The X-Axis Body Rate are negligible
• The vehicle is flying through a perfect gas

We predict the conditions at the leading edges of the fins by using the free stream conditions 

Now that the properties of the flow surrounding the fin have been ascertained, it is necessary to determine the boundary layer coefficients. These are typically empirical properties that describe the convective heat transfer from the flow to the vehicle.

Further Reading

 3.45483.pdf

16.unified/www/SPRING/propulsion/notes/node128.html