OAF139 AIRFOIL (oaf139-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: OAF139 AIRFOIL (oaf139-il) Reynolds number: 50,000 Max Cl/Cd: 13.34 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-oaf139-il-50000.txt Download as CSV file: xf-oaf139-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: OAF139 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.8283 0.12301 0.11517 0.0697 1.0000 0.2823
-10.000 -0.8208 0.11753 0.10965 0.0685 1.0000 0.2808
-9.750 -0.8278 0.11102 0.10313 0.0659 1.0000 0.2800
-9.500 -0.8445 0.10339 0.09549 0.0625 1.0000 0.2799
-9.250 -0.8745 0.09369 0.08583 0.0574 1.0000 0.2801
-9.000 -0.8575 0.09178 0.08388 0.0588 1.0000 0.2886
-8.750 -0.8981 0.08075 0.07290 0.0527 1.0000 0.2916
-8.500 -1.0216 0.05672 0.04854 0.0390 1.0000 0.2928
-8.250 -1.0195 0.05243 0.04403 0.0386 1.0000 0.3039
-8.000 -1.0166 0.04817 0.03944 0.0381 1.0000 0.3176
-7.750 -0.9918 0.04758 0.03886 0.0394 1.0000 0.3314
-7.500 -0.9622 0.04787 0.03926 0.0412 1.0000 0.3446
-7.250 -0.9400 0.04682 0.03817 0.0423 1.0000 0.3588
-7.000 -0.9200 0.04534 0.03661 0.0430 1.0000 0.3738
-6.750 -0.9001 0.04376 0.03493 0.0435 1.0000 0.3894
-6.500 -0.8794 0.04227 0.03332 0.0439 1.0000 0.4054
-6.250 -0.8581 0.04083 0.03175 0.0442 1.0000 0.4216
-6.000 -0.8283 0.04127 0.03234 0.0464 1.0000 0.4342
-5.750 -0.8031 0.04061 0.03167 0.0475 1.0000 0.4482
-5.500 -0.7798 0.03940 0.03042 0.0480 1.0000 0.4631
-5.250 -0.7567 0.03804 0.02898 0.0481 1.0000 0.4787
-5.000 -0.7333 0.03660 0.02743 0.0480 1.0000 0.4948
-4.750 -0.7063 0.03621 0.02711 0.0493 1.0000 0.5078
-4.500 -0.6803 0.03540 0.02633 0.0501 1.0000 0.5211
-4.250 -0.6550 0.03425 0.02515 0.0502 1.0000 0.5361
-4.000 -0.6296 0.03298 0.02384 0.0498 1.0000 0.5517
-3.750 -0.6034 0.03183 0.02266 0.0494 1.0000 0.5680
-3.500 -0.5759 0.03146 0.02242 0.0508 1.0000 0.5801
-3.250 -0.5488 0.03059 0.02159 0.0509 1.0000 0.5945
-3.000 -0.5214 0.02965 0.02070 0.0506 1.0000 0.6101
-2.750 -0.4932 0.02870 0.01979 0.0499 1.0000 0.6262
-2.500 -0.4641 0.02796 0.01913 0.0494 1.0000 0.6421
-2.250 -0.4341 0.02745 0.01882 0.0493 1.0000 0.6560
-2.000 -0.4018 0.02681 0.01834 0.0478 1.0000 0.6716
-1.750 -0.3668 0.02622 0.01794 0.0449 1.0000 0.6884
-1.500 -0.3405 0.02581 0.01768 0.0416 1.0000 0.7048
-1.250 -0.2735 0.02592 0.01781 0.0346 0.9313 0.7260
-1.000 -0.2434 0.02607 0.01789 0.0350 0.8838 0.7433
-0.750 -0.2241 0.02614 0.01790 0.0374 0.8470 0.7599
-0.500 -0.2063 0.02617 0.01787 0.0403 0.8169 0.7769
-0.250 -0.1860 0.02615 0.01782 0.0423 0.7881 0.7944
0.000 -0.1663 0.02618 0.01781 0.0451 0.7637 0.8114
0.250 -0.1428 0.02618 0.01781 0.0467 0.7382 0.8299
0.500 -0.1193 0.02617 0.01778 0.0483 0.7149 0.8494
0.750 -0.0935 0.02620 0.01780 0.0497 0.6927 0.8694
1.000 -0.0627 0.02631 0.01787 0.0503 0.6711 0.8897
1.250 -0.0215 0.02658 0.01817 0.0483 0.6458 0.9111
1.500 0.0251 0.02688 0.01845 0.0453 0.6209 0.9329
1.750 0.0791 0.02725 0.01873 0.0411 0.5965 0.9540
2.000 0.1460 0.02776 0.01929 0.0334 0.5654 0.9736
2.250 0.2071 0.02809 0.01955 0.0271 0.5390 0.9949
2.500 0.2341 0.02820 0.01963 0.0252 0.5201 1.0000
2.750 0.2475 0.02825 0.01966 0.0255 0.5044 1.0000
3.000 0.2605 0.02854 0.01997 0.0256 0.4885 1.0000
3.250 0.2726 0.02897 0.02038 0.0263 0.4734 1.0000
3.500 0.2877 0.02951 0.02084 0.0274 0.4588 1.0000
3.750 0.3080 0.03005 0.02125 0.0284 0.4439 1.0000
4.000 0.3317 0.03068 0.02177 0.0290 0.4279 1.0000
4.250 0.3583 0.03165 0.02274 0.0286 0.4103 1.0000
4.500 0.3853 0.03276 0.02390 0.0281 0.3929 1.0000
5.000 0.4394 0.03551 0.02678 0.0266 0.3595 1.0000
5.250 0.4657 0.03710 0.02846 0.0258 0.3438 1.0000
5.500 0.4915 0.03868 0.03009 0.0254 0.3299 1.0000
5.750 0.5166 0.03874 0.02993 0.0275 0.3186 1.0000
6.000 0.5416 0.04176 0.03328 0.0249 0.3035 1.0000
6.250 0.5636 0.04543 0.03723 0.0219 0.2901 1.0000
6.500 0.5854 0.04778 0.03965 0.0212 0.2795 1.0000
6.750 0.6069 0.04999 0.04194 0.0206 0.2686 1.0000
7.000 0.6084 0.05905 0.05139 0.0120 0.2607 1.0000
7.250 0.5938 0.07062 0.06317 -0.0001 0.2594 1.0000
7.500 0.5830 0.07919 0.07175 -0.0083 0.2613 1.0000
7.750 0.5786 0.08533 0.07788 -0.0123 0.2634 1.0000
8.000 0.5862 0.09034 0.08289 -0.0138 0.2655 1.0000
8.250 0.5059 0.10715 0.09964 -0.0342 0.3749 1.0000
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Polar data table (+)
Polar graphs
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