WORTMANN FX 2 AIRFOIL (fx2-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: WORTMANN FX 2 AIRFOIL (fx2-il) Reynolds number: 1,000,000 Max Cl/Cd: 107.14 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx2-il-1000000.txt Download as CSV file: xf-fx2-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 2 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-19.750 -0.6277 0.07555 0.07121 -0.1660 0.8272 0.0112
-19.500 -0.6328 0.07136 0.06690 -0.1684 0.8269 0.0113
-19.250 -0.6439 0.06677 0.06219 -0.1707 0.8265 0.0114
-19.000 -0.6369 0.06429 0.05964 -0.1725 0.8261 0.0113
-18.750 -0.6542 0.05933 0.05457 -0.1744 0.8256 0.0118
-18.500 -0.6532 0.05643 0.05159 -0.1759 0.8252 0.0119
-18.250 -0.6522 0.05363 0.04872 -0.1773 0.8249 0.0121
-18.000 -0.6469 0.05133 0.04635 -0.1785 0.8245 0.0123
-17.750 -0.6378 0.04942 0.04439 -0.1797 0.8241 0.0127
-17.500 -0.6356 0.04703 0.04192 -0.1806 0.8237 0.0127
-17.250 -0.6259 0.04533 0.04017 -0.1814 0.8233 0.0129
-17.000 -0.6194 0.04343 0.03819 -0.1821 0.8229 0.0131
-16.750 -0.6102 0.04179 0.03649 -0.1828 0.8225 0.0135
-16.500 -0.5995 0.04033 0.03496 -0.1834 0.8220 0.0137
-16.250 -0.5862 0.03912 0.03369 -0.1840 0.8216 0.0140
-16.000 -0.5748 0.03782 0.03232 -0.1844 0.8211 0.0143
-15.750 -0.5734 0.03590 0.03034 -0.1841 0.8205 0.0147
-15.500 -0.5649 0.03456 0.02897 -0.1840 0.8202 0.0150
-15.250 -0.5546 0.03340 0.02779 -0.1839 0.8201 0.0155
-15.000 -0.5446 0.03227 0.02661 -0.1835 0.8199 0.0158
-14.750 -0.5321 0.03132 0.02563 -0.1833 0.8197 0.0161
-14.500 -0.5194 0.03041 0.02469 -0.1830 0.8195 0.0168
-14.250 -0.5056 0.02960 0.02383 -0.1827 0.8193 0.0172
-14.000 -0.4918 0.02881 0.02300 -0.1823 0.8191 0.0175
-13.750 -0.4853 0.02765 0.02181 -0.1813 0.8189 0.0182
-13.500 -0.4745 0.02676 0.02091 -0.1805 0.8186 0.0191
-13.250 -0.4616 0.02602 0.02015 -0.1799 0.8183 0.0195
-13.000 -0.4486 0.02531 0.01941 -0.1792 0.8179 0.0203
-12.750 -0.4322 0.02479 0.01887 -0.1787 0.8175 0.0211
-12.500 -0.4219 0.02399 0.01804 -0.1776 0.8171 0.0220
-12.250 -0.4099 0.02331 0.01736 -0.1766 0.8167 0.0231
-12.000 -0.3958 0.02275 0.01680 -0.1757 0.8164 0.0241
-11.750 -0.3805 0.02227 0.01630 -0.1749 0.8160 0.0255
-11.500 -0.3685 0.02166 0.01569 -0.1737 0.8156 0.0272
-11.250 -0.3549 0.02116 0.01521 -0.1726 0.8152 0.0292
-11.000 -0.3400 0.02074 0.01477 -0.1717 0.8148 0.0309
-10.750 -0.3270 0.02026 0.01433 -0.1704 0.8144 0.0341
-10.500 -0.3105 0.01992 0.01400 -0.1696 0.8140 0.0368
-10.250 -0.2975 0.01947 0.01357 -0.1682 0.8136 0.0399
-10.000 -0.2820 0.01913 0.01324 -0.1672 0.8132 0.0426
-9.750 -0.2645 0.01886 0.01296 -0.1663 0.8128 0.0443
-9.500 -0.2525 0.01842 0.01253 -0.1648 0.8124 0.0472
-9.250 -0.2372 0.01809 0.01223 -0.1636 0.8120 0.0499
-9.000 -0.2209 0.01782 0.01195 -0.1625 0.8116 0.0520
-8.750 -0.2037 0.01758 0.01170 -0.1616 0.8112 0.0533
-8.500 -0.1932 0.01712 0.01124 -0.1596 0.8106 0.0563
-8.250 -0.1799 0.01674 0.01088 -0.1581 0.8100 0.0591
-8.000 -0.1652 0.01643 0.01056 -0.1567 0.8095 0.0612
-7.750 -0.1496 0.01618 0.01029 -0.1554 0.8090 0.0630
-7.500 -0.1354 0.01588 0.00998 -0.1538 0.8086 0.0649
-7.250 -0.1257 0.01546 0.00957 -0.1516 0.8080 0.0688
-7.000 -0.1146 0.01510 0.00922 -0.1496 0.8075 0.0721
-6.750 -0.1022 0.01481 0.00892 -0.1477 0.8070 0.0747
-6.500 -0.0933 0.01455 0.00866 -0.1452 0.8063 0.0795
-6.250 -0.0955 0.01442 0.00856 -0.1407 0.8053 0.0854
-6.000 -0.1042 0.01439 0.00858 -0.1351 0.8042 0.0940
-5.750 -0.1024 0.01386 0.00822 -0.1315 0.8036 0.1332
-5.500 -0.0995 0.01326 0.00789 -0.1282 0.8027 0.1937
-5.250 -0.0958 0.01257 0.00757 -0.1251 0.8017 0.2809
-5.000 -0.0889 0.01178 0.00723 -0.1226 0.8006 0.3910
-4.750 -0.0772 0.01103 0.00698 -0.1209 0.7995 0.5214
-4.500 -0.0557 0.01108 0.00710 -0.1202 0.7986 0.5526
-4.250 -0.0331 0.01116 0.00720 -0.1197 0.7976 0.5697
-4.000 -0.0085 0.01119 0.00726 -0.1195 0.7967 0.5840
-3.750 0.0158 0.01128 0.00737 -0.1192 0.7960 0.5933
-3.500 0.0405 0.01140 0.00748 -0.1190 0.7953 0.6021
-3.250 0.0657 0.01152 0.00764 -0.1189 0.7946 0.6126
-3.000 0.0920 0.01168 0.00782 -0.1189 0.7941 0.6230
-2.750 0.1196 0.01181 0.00792 -0.1193 0.7935 0.6311
-2.500 0.1478 0.01193 0.00805 -0.1197 0.7930 0.6367
-2.250 0.1765 0.01209 0.00819 -0.1201 0.7925 0.6428
-2.000 0.2053 0.01224 0.00830 -0.1207 0.7920 0.6477
-1.750 0.1236 0.01410 0.01024 -0.0996 0.7808 0.6496
-1.500 0.1518 0.01419 0.01034 -0.1000 0.7800 0.6525
-1.250 0.1823 0.01421 0.01035 -0.1008 0.7796 0.6549
-1.000 0.2131 0.01426 0.01039 -0.1017 0.7791 0.6585
-0.750 0.2453 0.01428 0.01037 -0.1028 0.7788 0.6617
-0.500 0.1915 0.01643 0.01252 -0.0885 0.7671 0.6636
-0.250 0.2199 0.01645 0.01256 -0.0889 0.7661 0.6656
0.000 0.2493 0.01644 0.01255 -0.0896 0.7654 0.6670
0.250 0.2802 0.01638 0.01249 -0.0905 0.7650 0.6685
0.500 0.3114 0.01632 0.01243 -0.0914 0.7645 0.6700
0.750 0.3439 0.01621 0.01232 -0.0926 0.7642 0.6717
1.000 0.3761 0.01609 0.01220 -0.0937 0.7639 0.6735
1.250 0.4080 0.01598 0.01209 -0.0948 0.7636 0.6752
1.500 0.4410 0.01584 0.01194 -0.0961 0.7633 0.6768
1.750 0.4746 0.01568 0.01177 -0.0975 0.7632 0.6780
2.000 0.5098 0.01535 0.01146 -0.0991 0.7631 0.6798
2.250 0.5479 0.01496 0.01109 -0.1013 0.7633 0.6812
2.500 0.5907 0.01444 0.01060 -0.1042 0.7636 0.6824
2.750 0.6368 0.01387 0.01005 -0.1079 0.7640 0.6836
3.000 0.6964 0.01297 0.00917 -0.1141 0.7650 0.6848
3.250 0.7663 0.01193 0.00816 -0.1226 0.7658 0.6858
3.500 0.8375 0.01102 0.00725 -0.1315 0.7655 0.6870
3.750 0.8814 0.01058 0.00682 -0.1350 0.7642 0.6884
4.000 0.9282 0.01008 0.00632 -0.1391 0.7628 0.6898
4.250 0.9743 0.00963 0.00587 -0.1431 0.7610 0.6911
4.500 0.9619 0.00970 0.00599 -0.1348 0.7564 0.6927
4.750 0.9654 0.00974 0.00605 -0.1300 0.7520 0.6939
5.000 0.9964 0.00930 0.00562 -0.1308 0.7481 0.6954
5.250 0.9783 0.00979 0.00617 -0.1219 0.7412 0.6970
5.500 0.9830 0.01000 0.00642 -0.1177 0.7341 0.6983
5.750 0.9585 0.01123 0.00768 -0.1085 0.7217 0.6997
6.000 0.9662 0.01169 0.00815 -0.1052 0.7080 0.7009
6.250 0.9937 0.01132 0.00763 -0.1051 0.6769 0.7021
6.500 0.9874 0.01211 0.00821 -0.0992 0.6389 0.7034
6.750 0.9751 0.01327 0.00920 -0.0925 0.6075 0.7047
7.000 0.9590 0.01467 0.01041 -0.0854 0.5714 0.7059
7.250 0.9491 0.01598 0.01157 -0.0795 0.5379 0.7071
7.500 0.9343 0.01756 0.01290 -0.0731 0.4909 0.7081
7.750 0.9308 0.01881 0.01397 -0.0686 0.4546 0.7089
8.000 0.9284 0.02007 0.01499 -0.0644 0.4100 0.7096
8.250 0.9281 0.02126 0.01597 -0.0607 0.3677 0.7104
8.500 0.9323 0.02226 0.01677 -0.0577 0.3271 0.7116
8.750 0.9339 0.02344 0.01768 -0.0544 0.2752 0.7125
9.000 0.9372 0.02460 0.01857 -0.0515 0.2242 0.7133
9.250 0.9436 0.02568 0.01944 -0.0491 0.1850 0.7140
9.500 0.9530 0.02665 0.02025 -0.0471 0.1551 0.7147
9.750 0.9643 0.02753 0.02101 -0.0455 0.1282 0.7154
10.250 0.9863 0.02942 0.02263 -0.0422 0.0809 0.7167
10.500 1.0019 0.03015 0.02335 -0.0412 0.0747 0.7174
10.750 1.0167 0.03094 0.02412 -0.0401 0.0681 0.7180
11.000 1.0339 0.03158 0.02478 -0.0394 0.0642 0.7186
11.250 1.0486 0.03239 0.02556 -0.0384 0.0573 0.7193
11.500 1.0656 0.03307 0.02624 -0.0377 0.0520 0.7201
11.750 1.0777 0.03406 0.02715 -0.0364 0.0398 0.7208
12.000 1.0888 0.03516 0.02817 -0.0351 0.0299 0.7215
12.250 1.1013 0.03619 0.02919 -0.0340 0.0252 0.7222
12.500 1.1139 0.03724 0.03024 -0.0328 0.0223 0.7227
12.750 1.1287 0.03814 0.03117 -0.0320 0.0213 0.7233
13.000 1.1406 0.03926 0.03231 -0.0310 0.0199 0.7238
13.250 1.1515 0.04048 0.03355 -0.0298 0.0185 0.7243
13.500 1.1657 0.04146 0.03458 -0.0291 0.0179 0.7247
13.750 1.1788 0.04256 0.03572 -0.0282 0.0172 0.7253
14.000 1.1905 0.04379 0.03700 -0.0273 0.0166 0.7257
14.250 1.2018 0.04503 0.03827 -0.0264 0.0161 0.7266
14.500 1.2078 0.04675 0.04004 -0.0251 0.0151 0.7273
14.750 1.2186 0.04809 0.04145 -0.0243 0.0149 0.7281
15.000 1.2306 0.04935 0.04277 -0.0236 0.0145 0.7287
15.250 1.2413 0.05075 0.04423 -0.0229 0.0141 0.7295
15.500 1.2511 0.05225 0.04579 -0.0222 0.0137 0.7302
15.750 1.2621 0.05366 0.04724 -0.0216 0.0132 0.7307
16.000 1.2698 0.05542 0.04906 -0.0209 0.0129 0.7312
16.250 1.2744 0.05752 0.05121 -0.0200 0.0124 0.7316
16.500 1.2724 0.06033 0.05411 -0.0189 0.0121 0.7319
16.750 1.2814 0.06207 0.05592 -0.0186 0.0119 0.7324
17.000 1.2894 0.06396 0.05788 -0.0182 0.0117 0.7328
17.250 1.2962 0.06600 0.06000 -0.0179 0.0115 0.7332
17.500 1.3029 0.06809 0.06216 -0.0176 0.0113 0.7336
17.750 1.3082 0.07036 0.06451 -0.0174 0.0111 0.7340
18.000 1.3127 0.07278 0.06700 -0.0172 0.0108 0.7344
18.250 1.3179 0.07512 0.06941 -0.0172 0.0106 0.7349
18.500 1.3212 0.07775 0.07212 -0.0172 0.0105 0.7353
18.750 1.3242 0.08046 0.07490 -0.0174 0.0102 0.7357
19.000 1.3255 0.08342 0.07794 -0.0177 0.0101 0.7360
19.250 1.3247 0.08672 0.08132 -0.0180 0.0100 0.7364
|
Polar data table (+)
Polar graphs
<< Back to WORTMANN FX 2 AIRFOIL (fx2-il)