WORTMANN FX 62-K-131 AIRFOIL (fx62k131-il) Xfoil prediction polar at RE=500,000 Ncrit=0
| Details | Polar file |
|---|---|
|
Airfoil: WORTMANN FX 62-K-131 AIRFOIL (fx62k131-il) Reynolds number: 500,000 Max Cl/Cd: 123.98 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx62k131-il-500000.txt Download as CSV file: xf-fx62k131-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 62-K-131 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -0.1797 0.13856 0.13640 -0.0652 0.9894 0.0098
-14.000 -0.1737 0.13575 0.13357 -0.0677 0.9881 0.0101
-13.750 -0.1676 0.13274 0.13055 -0.0704 0.9869 0.0102
-13.500 -0.1619 0.12955 0.12736 -0.0732 0.9851 0.0103
-13.250 -0.1567 0.12639 0.12420 -0.0752 0.9797 0.0104
-13.000 -0.1491 0.12287 0.12067 -0.0777 0.9761 0.0105
-12.750 -0.1414 0.11919 0.11698 -0.0802 0.9725 0.0105
-12.500 -0.1344 0.11545 0.11324 -0.0825 0.9676 0.0105
-12.250 -0.1264 0.11141 0.10919 -0.0852 0.9640 0.0105
-12.000 -0.1183 0.10730 0.10507 -0.0880 0.9607 0.0106
-11.750 -0.1112 0.10311 0.10087 -0.0906 0.9558 0.0106
-11.500 -0.1104 0.09739 0.09516 -0.0925 0.9517 0.0111
-11.250 -0.1006 0.09372 0.09147 -0.0946 0.9469 0.0114
-11.000 -0.0918 0.08989 0.08761 -0.0968 0.9404 0.0117
-10.750 -0.0850 0.08610 0.08379 -0.0988 0.9340 0.0121
-10.500 -0.0804 0.08228 0.07994 -0.1004 0.9265 0.0123
-10.250 -0.0767 0.07842 0.07604 -0.1020 0.9200 0.0127
-10.000 -0.0749 0.07459 0.07219 -0.1033 0.9131 0.0130
-9.750 -0.0732 0.07055 0.06810 -0.1049 0.9075 0.0135
-9.500 -0.0726 0.06646 0.06401 -0.1064 0.9018 0.0138
-9.250 -0.0735 0.06228 0.05981 -0.1079 0.8965 0.0142
-9.000 -0.0742 0.05779 0.05529 -0.1100 0.8921 0.0145
-8.750 -0.0763 0.05299 0.05050 -0.1125 0.8872 0.0149
-8.500 -0.0788 0.04748 0.04498 -0.1164 0.8827 0.0152
-8.250 -0.0873 0.04111 0.03856 -0.1222 0.8782 0.0147
-8.000 -0.0981 0.03565 0.03303 -0.1275 0.8729 0.0145
-7.750 -0.1083 0.03159 0.02885 -0.1308 0.8678 0.0146
-7.500 -0.1042 0.02738 0.02441 -0.1349 0.8638 0.0156
-7.250 -0.0877 0.02547 0.02224 -0.1365 0.8597 0.0166
-7.000 -0.0770 0.02219 0.01870 -0.1380 0.8558 0.0167
-6.750 -0.0756 0.01470 0.01075 -0.1408 0.8525 0.0176
-6.500 -0.0579 0.01227 0.00823 -0.1419 0.8495 0.0187
-6.250 -0.0366 0.01075 0.00658 -0.1428 0.8462 0.0203
-6.000 -0.0112 0.00973 0.00536 -0.1434 0.8433 0.0241
-5.750 0.0194 0.01006 0.00538 -0.1434 0.8403 0.0260
-5.250 0.0706 0.01795 0.01215 -0.1526 0.8429 0.0174
-5.000 0.0968 0.01536 0.00939 -0.1522 0.8404 0.0144
-4.750 0.1245 0.01402 0.00789 -0.1521 0.8379 0.0143
-4.500 0.1519 0.01315 0.00695 -0.1521 0.8351 0.0153
-4.250 0.1804 0.01260 0.00633 -0.1525 0.8318 0.0165
-4.000 0.2125 0.01152 0.00517 -0.1542 0.8286 0.0199
-3.750 0.2457 0.01099 0.00456 -0.1557 0.8257 0.0230
-3.500 0.2798 0.01055 0.00400 -0.1574 0.8231 0.0302
-3.250 0.3413 0.00820 0.00328 -0.1680 0.8211 0.4973
-3.000 0.3774 0.00795 0.00340 -0.1702 0.8184 0.6311
-2.750 0.4066 0.00804 0.00353 -0.1704 0.8154 0.6686
-2.500 0.4346 0.00825 0.00371 -0.1702 0.8128 0.6946
-2.250 0.4616 0.00851 0.00392 -0.1698 0.8103 0.7114
-2.000 0.4874 0.00874 0.00415 -0.1692 0.8073 0.7223
-1.750 0.5159 0.00882 0.00419 -0.1694 0.8041 0.7284
-1.500 0.5447 0.00887 0.00419 -0.1697 0.8009 0.7330
-1.250 0.5724 0.00895 0.00424 -0.1697 0.7981 0.7364
-0.750 0.6317 0.00907 0.00428 -0.1709 0.7920 0.7456
-0.500 0.6580 0.00914 0.00436 -0.1705 0.7883 0.7484
-0.250 0.6854 0.00921 0.00442 -0.1705 0.7851 0.7519
0.000 0.7152 0.00927 0.00443 -0.1710 0.7822 0.7560
0.250 0.7446 0.00931 0.00448 -0.1716 0.7785 0.7603
0.500 0.7702 0.00936 0.00456 -0.1711 0.7742 0.7631
0.750 0.7976 0.00939 0.00458 -0.1710 0.7700 0.7663
1.000 0.8262 0.00941 0.00459 -0.1713 0.7652 0.7701
1.250 0.8560 0.00940 0.00460 -0.1720 0.7597 0.7741
1.500 0.8831 0.00941 0.00461 -0.1718 0.7556 0.7762
1.750 0.9098 0.00945 0.00468 -0.1717 0.7510 0.7786
2.000 0.9372 0.00946 0.00473 -0.1718 0.7456 0.7814
2.250 0.9668 0.00947 0.00474 -0.1723 0.7409 0.7847
2.500 0.9961 0.00948 0.00480 -0.1729 0.7348 0.7881
2.750 1.0226 0.00947 0.00483 -0.1727 0.7290 0.7900
3.000 1.0491 0.00950 0.00490 -0.1725 0.7230 0.7922
3.250 1.0759 0.00952 0.00499 -0.1724 0.7160 0.7948
3.500 1.1038 0.00954 0.00505 -0.1726 0.7086 0.7978
3.750 1.1323 0.00955 0.00505 -0.1729 0.6975 0.8012
4.000 1.1563 0.00953 0.00506 -0.1721 0.6800 0.8033
4.250 1.1800 0.00958 0.00514 -0.1713 0.6619 0.8054
4.500 1.2038 0.00971 0.00525 -0.1705 0.6432 0.8078
4.750 1.2267 0.00991 0.00540 -0.1697 0.6166 0.8107
5.000 1.2492 0.01022 0.00561 -0.1688 0.5852 0.8138
5.250 1.2674 0.01073 0.00592 -0.1671 0.5412 0.8164
5.500 1.2824 0.01131 0.00632 -0.1648 0.4968 0.8186
5.750 1.2957 0.01202 0.00683 -0.1622 0.4464 0.8211
6.000 1.3044 0.01301 0.00749 -0.1590 0.3788 0.8240
6.250 1.3091 0.01430 0.00833 -0.1552 0.3024 0.8270
6.500 1.3128 0.01546 0.00914 -0.1513 0.2378 0.8300
6.750 1.3103 0.01696 0.01021 -0.1464 0.1621 0.8324
7.000 1.3141 0.01827 0.01123 -0.1427 0.1124 0.8350
7.250 1.3211 0.01947 0.01224 -0.1397 0.0757 0.8376
7.500 1.3269 0.02084 0.01338 -0.1368 0.0410 0.8403
7.750 1.3308 0.02246 0.01483 -0.1336 0.0137 0.8430
8.000 1.3380 0.02373 0.01616 -0.1307 0.0081 0.8452
8.250 1.3499 0.02472 0.01729 -0.1287 0.0073 0.8475
8.500 1.3616 0.02579 0.01846 -0.1268 0.0066 0.8498
8.750 1.3727 0.02697 0.01971 -0.1249 0.0059 0.8522
9.000 1.3786 0.02863 0.02148 -0.1226 0.0051 0.8548
9.250 1.3861 0.03023 0.02319 -0.1205 0.0049 0.8572
9.500 1.3939 0.03167 0.02475 -0.1184 0.0047 0.8591
9.750 1.3992 0.03336 0.02657 -0.1162 0.0046 0.8611
10.000 1.4044 0.03513 0.02846 -0.1140 0.0044 0.8634
10.250 1.4093 0.03700 0.03045 -0.1119 0.0042 0.8657
10.500 1.4138 0.03895 0.03251 -0.1099 0.0041 0.8681
10.750 1.4178 0.04103 0.03471 -0.1080 0.0039 0.8701
11.000 1.4207 0.04316 0.03696 -0.1060 0.0038 0.8719
11.250 1.4228 0.04535 0.03931 -0.1039 0.0037 0.8739
11.500 1.4247 0.04762 0.04172 -0.1019 0.0036 0.8759
11.750 1.4269 0.04998 0.04419 -0.1001 0.0034 0.8780
12.000 1.4281 0.05252 0.04687 -0.0982 0.0034 0.8800
12.250 1.4298 0.05511 0.04962 -0.0964 0.0034 0.8819
12.500 1.4303 0.05799 0.05267 -0.0946 0.0033 0.8838
12.750 1.4301 0.06095 0.05584 -0.0927 0.0033 0.8856
13.000 1.4277 0.06428 0.05942 -0.0907 0.0034 0.8872
13.250 1.4194 0.06879 0.06430 -0.0881 0.0037 0.8886
13.500 1.4036 0.07443 0.07035 -0.0860 0.0040 0.8899
13.750 1.3849 0.08043 0.07667 -0.0849 0.0042 0.8912
14.000 1.3673 0.08629 0.08279 -0.0847 0.0043 0.8928
14.250 1.3479 0.09270 0.08945 -0.0852 0.0045 0.8943
14.500 1.3292 0.09921 0.09618 -0.0866 0.0046 0.8960
14.750 1.3098 0.10626 0.10343 -0.0888 0.0047 0.8976
15.000 1.2862 0.11450 0.11188 -0.0919 0.0048 0.8989
15.250 1.0711 0.10143 0.09868 -0.0638 0.0040 0.8855
15.500 1.0509 0.10679 0.10424 -0.0658 0.0041 0.8863
15.750 1.0301 0.11244 0.11008 -0.0683 0.0041 0.8872
16.000 1.0099 0.11829 0.11609 -0.0712 0.0042 0.8881
16.250 0.9905 0.12437 0.12232 -0.0745 0.0042 0.8889
16.500 0.9692 0.13094 0.12905 -0.0782 0.0043 0.8897
16.750 0.9511 0.13743 0.13567 -0.0821 0.0043 0.8905
|
Polar data table (+)
Polar graphs
<< Back to WORTMANN FX 62-K-131 AIRFOIL (fx62k131-il)