[sharkforce]

I want to import the experimental pressure coef data from http://www.grc.nasa.gov/WWW/wind/val...ng/m6wing.html

into CFD-post, and compare with the fluent results. I finally figured out how to make a poly line from a intersecting plane and the wing to get the pressure data vs x.

however I still need figure out three things:
1) how do I create a variable for x/l
2) how do I import the the exp data on each wing surface when for ex the upper wing surface looks like this at eta = 0.2 (see below):
3) ultimately make a chart with cp vs x/l with both the fluent result and the experimental results


0.9503000 -0.1010000 0.02 0.02
0.8159700 7.9000004E-02 0.02 0.02
0.6659300 0.1710000 0.02 0.02
0.5658800 0.2290000 0.02 0.02
0.4659900 0.2630000 0.02 0.02
0.3658000 0.2150000 0.02 0.02
0.2657900 0.1640000 0.02 0.02
0.1659400 9.2000000E-02 0.02 0.02
4.9929999E-02 4.6000000E-02 0.02 0.02
2.0020001E-02 3.4000002E-02 0.02 0.02
5.9300000E-03 -0.5490000 0.02 0.02
3.4000000E-04 -0.8010000 0.02 0.02