How can I load a Cp airfoil specific distribution to a mesh

Hi! 

The problem is the following, I am looking to introduce a pressure distribution onto an airfoil. 

I have the Cp values for specific points that doesn´t match my mesh nodes because they were not obtained through a CFD of the airfoil. 

The problem is the same for the Cf values. 

I will attach the excel with the values. 

At first I thought graphing this values, dividing them into functions that I could aproxximate well with trend lines and introduce this functions into the respective nodes that I was selecting by hand. This demands a lot of time and at the end I discovered that the trend lines were not good enough unless I use 15 decimals, thing that exceeds the space to put equations by hypermesh. 

I will attach the model also 

PS: I dont know why I cant load any images.

Hope you understood and thank you for your time.