S6063 7.05% (s6063-il)
S6063 7.05% - Selig S6063 low Reynolds number airfoil
| Details | Dat file | Parser | |
|
(s6063-il) S6063 7.05% Selig S6063 low Reynolds number airfoil Max thickness 7% at 29.4% chord. Max camber 1.3% at 43.8% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
S6063 7.05%
1.00000 0.00000
0.99687 0.00017
0.98758 0.00078
0.97238 0.00197
0.95160 0.00383
0.92565 0.00638
0.89500 0.00956
0.86012 0.01328
0.82151 0.01739
0.77969 0.02175
0.73513 0.02617
0.68835 0.03050
0.63984 0.03457
0.59007 0.03827
0.53954 0.04152
0.48881 0.04424
0.43838 0.04633
0.38877 0.04774
0.34047 0.04838
0.29396 0.04823
0.24968 0.04725
0.20803 0.04544
0.16941 0.04280
0.13413 0.03938
0.10252 0.03523
0.07481 0.03044
0.05123 0.02513
0.03194 0.01943
0.01708 0.01355
0.00671 0.00772
0.00088 0.00242
0.00058 -0.00190
0.00605 -0.00588
0.01660 -0.00982
0.03215 -0.01333
0.05261 -0.01630
0.07786 -0.01867
0.10771 -0.02042
0.14190 -0.02156
0.18013 -0.02215
0.22201 -0.02222
0.26710 -0.02184
0.31491 -0.02109
0.36490 -0.02001
0.41652 -0.01865
0.46919 -0.01706
0.52232 -0.01530
0.57532 -0.01342
0.62759 -0.01147
0.67854 -0.00952
0.72758 -0.00761
0.77415 -0.00581
0.81769 -0.00418
0.85768 -0.00278
0.89359 -0.00164
0.92495 -0.00081
0.95132 -0.00026
0.97231 0.00002
0.98758 0.00009
0.99688 0.00004
1.00000 0.00000
|
No parser warnings |
Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
|
Polars for S6063 7.05% (s6063-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s6063-il | 50,000 | 9 | 34.7 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s6063-il | 50,000 | 5 | 34.7 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s6063-il | 100,000 | 9 | 48.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s6063-il | 100,000 | 5 | 45.3 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s6063-il | 200,000 | 9 | 61.5 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s6063-il | 200,000 | 5 | 53.4 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s6063-il | 500,000 | 9 | 74.8 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s6063-il | 500,000 | 5 | 60.2 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s6063-il | 1,000,000 | 9 | 81.3 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s6063-il | 1,000,000 | 5 | 68.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||