It wasn't readable so this time I pasted into notepad to convert it to plain text and then still had to add formatting. It should be in straight ascii now.
The numbers are based on the CL values of the AS5045 airfoil taken from the graph http://www.krnet.org/as504x/repeat_1m.gif The predicted best glide is CL = 0.72 at AoA of 5 degrees. The predicted stall is CL=1.2 at AoA of 14 degrees. Predicted best glide Predicted stall std KR2 predicted stall altitude rho lb s^2/ft^4 900 | 1200 | 1800 | 2400 | 900 | 1200 | 1800 | 2400 | 900 0 | 0.0023769 | 79.2 | 91.4 | 112.0 | 129.3 | 61.3 | 70.8 | 86.7 | 100.1 | 51.5 1000 | 0.0023081 | 80.3 | 92.8 | 113.6 | 131.2 | 62.2 | 71.9 | 88.0 | 101.6 | 52.3 2000 | 0.0022409 | 81.5 | 94.2 | 115.3 | 133.2 | 63.2 | 72.9 | 89.3 | 103.1 | 53.1 4000 | 0.0021110 | 84.0 | 97.0 | 118.8 | 137.2 | 65.1 | 75.1 | 92.0 | 106.3 | 54.7 8000 | 0.0018685 | 89.3 |103.1 | 126.3 | 145.8 | 69.2 | 79.9 | 97.8 | 113.0 | 58.1 > > Hopefully the data below is readable I copied and pasted from excel. All
