WORTMANN FX 62-K-131 AIRFOIL (fx62k131-il) Xfoil prediction polar at RE=200,000 Ncrit=0
| Details | Polar file |
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Airfoil: WORTMANN FX 62-K-131 AIRFOIL (fx62k131-il) Reynolds number: 200,000 Max Cl/Cd: 83.65 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx62k131-il-200000.txt Download as CSV file: xf-fx62k131-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.1813 0.11879 0.11558 -0.0704 0.9776 0.0276
-11.500 -0.1691 0.11519 0.11197 -0.0721 0.9761 0.0287
-11.250 -0.1598 0.11148 0.10825 -0.0744 0.9749 0.0299
-11.000 -0.1508 0.10751 0.10427 -0.0771 0.9738 0.0311
-10.750 -0.1481 0.10420 0.10097 -0.0783 0.9693 0.0325
-10.500 -0.1429 0.10022 0.09699 -0.0808 0.9668 0.0342
-10.250 -0.1408 0.09586 0.09264 -0.0849 0.9647 0.0364
-9.250 -0.1242 0.07777 0.07460 -0.0945 0.9551 0.0406
-9.000 -0.1148 0.07379 0.07061 -0.0966 0.9528 0.0424
-8.750 -0.1079 0.06909 0.06591 -0.0999 0.9511 0.0442
-8.500 -0.1023 0.06374 0.06056 -0.1046 0.9495 0.0462
-8.250 -0.1046 0.05861 0.05545 -0.1088 0.9458 0.0477
-7.500 -0.1423 0.04467 0.04138 -0.1207 0.9255 0.0489
-7.250 -0.1562 0.04203 0.03841 -0.1237 0.9175 0.0500
-6.500 -0.1716 0.04686 0.04250 -0.1313 0.9128 0.0525
-6.250 -0.1468 0.04376 0.03940 -0.1335 0.9107 0.0559
-6.000 -0.1151 0.04028 0.03528 -0.1384 0.9085 0.0659
-5.750 -0.1086 0.03843 0.03352 -0.1361 0.9021 0.0684
-5.500 -0.0808 0.03603 0.03072 -0.1386 0.8986 0.0803
-5.250 -0.0465 0.03338 0.02788 -0.1420 0.8969 0.0948
-5.000 0.0042 0.02722 0.02063 -0.1419 0.8959 0.0354
-4.750 0.0427 0.02394 0.01692 -0.1436 0.8947 0.0306
-4.500 0.0798 0.02227 0.01502 -0.1451 0.8935 0.0322
-4.250 0.0896 0.02203 0.01470 -0.1420 0.8861 0.0345
-4.000 0.1220 0.02067 0.01321 -0.1425 0.8838 0.0352
-3.750 0.1577 0.01954 0.01201 -0.1439 0.8820 0.0372
-3.500 0.1997 0.01815 0.01065 -0.1474 0.8806 0.0467
-3.250 0.2719 0.01477 0.00960 -0.1593 0.8810 0.6335
-3.000 0.2874 0.01557 0.01040 -0.1559 0.8758 0.6896
-2.750 0.2987 0.01649 0.01129 -0.1512 0.8705 0.7184
-2.500 0.3076 0.01754 0.01232 -0.1449 0.8670 0.7455
-2.250 0.3070 0.01856 0.01336 -0.1380 0.8601 0.7605
-2.000 0.3222 0.01903 0.01376 -0.1345 0.8558 0.7741
-1.750 0.3438 0.01908 0.01372 -0.1323 0.8532 0.7794
-1.500 0.3829 0.01895 0.01343 -0.1348 0.8516 0.7881
-1.250 0.3863 0.01948 0.01396 -0.1302 0.8431 0.7928
-1.000 0.4214 0.01936 0.01374 -0.1318 0.8406 0.8001
-0.750 0.4504 0.01920 0.01351 -0.1316 0.8384 0.8051
-0.500 0.4641 0.01962 0.01390 -0.1294 0.8309 0.8118
-0.250 0.4954 0.01951 0.01373 -0.1302 0.8276 0.8175
0.000 0.5243 0.01932 0.01349 -0.1300 0.8251 0.8222
0.250 0.5625 0.01918 0.01329 -0.1323 0.8229 0.8287
0.500 0.5708 0.01952 0.01366 -0.1288 0.8143 0.8337
0.750 0.6032 0.01931 0.01341 -0.1296 0.8117 0.8389
1.000 0.6431 0.01907 0.01313 -0.1322 0.8097 0.8438
1.250 0.6524 0.01938 0.01349 -0.1289 0.8009 0.8482
1.500 0.6863 0.01911 0.01321 -0.1300 0.7979 0.8526
1.750 0.7283 0.01882 0.01288 -0.1330 0.7957 0.8570
2.000 0.7397 0.01897 0.01310 -0.1300 0.7866 0.8609
2.250 0.7735 0.01857 0.01271 -0.1309 0.7833 0.8647
2.500 0.8018 0.01860 0.01278 -0.1315 0.7764 0.8691
2.750 0.8325 0.01834 0.01254 -0.1320 0.7713 0.8724
3.000 0.8645 0.01794 0.01215 -0.1325 0.7682 0.8757
3.250 0.8852 0.01807 0.01239 -0.1316 0.7596 0.8801
3.500 0.9235 0.01775 0.01209 -0.1337 0.7556 0.8834
3.750 0.9448 0.01770 0.01213 -0.1326 0.7479 0.8871
4.000 0.9744 0.01736 0.01187 -0.1327 0.7425 0.8906
4.250 1.0023 0.01726 0.01186 -0.1329 0.7353 0.8942
4.500 1.0371 0.01703 0.01170 -0.1344 0.7289 0.8977
4.750 1.0588 0.01685 0.01162 -0.1332 0.7207 0.9013
5.000 1.0894 0.01643 0.01129 -0.1335 0.7137 0.9046
5.250 1.1164 0.01603 0.01098 -0.1331 0.7011 0.9084
5.500 1.1460 0.01554 0.01053 -0.1332 0.6862 0.9119
5.750 1.1669 0.01523 0.01031 -0.1316 0.6721 0.9155
6.000 1.1912 0.01504 0.01020 -0.1308 0.6572 0.9191
6.250 1.2134 0.01501 0.01030 -0.1298 0.6369 0.9232
6.500 1.2332 0.01489 0.01018 -0.1281 0.6098 0.9270
6.750 1.2498 0.01494 0.01019 -0.1258 0.5790 0.9310
7.000 1.2660 0.01525 0.01038 -0.1237 0.5410 0.9350
7.250 1.2758 0.01578 0.01074 -0.1206 0.4955 0.9394
7.500 1.2781 0.01645 0.01122 -0.1162 0.4476 0.9447
7.750 1.2823 0.01749 0.01205 -0.1127 0.3940 0.9497
8.000 1.2791 0.01873 0.01303 -0.1082 0.3400 0.9554
8.250 1.2724 0.02048 0.01441 -0.1038 0.2742 0.9619
8.500 1.2627 0.02246 0.01598 -0.0993 0.2048 0.9690
8.750 1.2550 0.02468 0.01778 -0.0956 0.1424 0.9773
9.000 1.2498 0.02684 0.01965 -0.0924 0.0920 0.9998
9.250 1.2484 0.02959 0.02204 -0.0904 0.0461 0.9999
9.500 1.2432 0.03283 0.02516 -0.0877 0.0240 0.9999
9.750 1.2431 0.03567 0.02814 -0.0858 0.0194 0.9999
10.000 1.2486 0.03803 0.03065 -0.0844 0.0171 0.9999
10.250 1.2536 0.04044 0.03318 -0.0832 0.0158 0.9999
10.500 1.2575 0.04298 0.03581 -0.0818 0.0149 0.9999
10.750 1.2604 0.04571 0.03863 -0.0800 0.0142 0.9999
11.000 1.2699 0.04832 0.04133 -0.0778 0.0136 0.9999
11.250 1.2910 0.05054 0.04369 -0.0764 0.0133 0.9999
11.500 1.3118 0.05293 0.04630 -0.0754 0.0132 0.9999
11.750 1.3239 0.05540 0.04904 -0.0745 0.0129 0.9999
12.000 1.3313 0.05795 0.05185 -0.0736 0.0123 0.9999
12.250 1.3367 0.06085 0.05502 -0.0727 0.0118 0.9999
12.500 1.3385 0.06386 0.05832 -0.0718 0.0110 0.9999
12.750 1.3374 0.06769 0.06245 -0.0708 0.0109 0.9999
13.000 1.3313 0.07214 0.06723 -0.0698 0.0110 0.9999
13.250 1.3212 0.07693 0.07233 -0.0691 0.0111 0.9999
13.500 1.3082 0.08206 0.07777 -0.0688 0.0113 0.9999
13.750 1.2926 0.08767 0.08367 -0.0691 0.0114 0.9999
14.000 1.2759 0.09360 0.08987 -0.0701 0.0115 0.9999
14.250 1.2581 0.10004 0.09656 -0.0719 0.0117 0.9999
14.500 1.2405 0.10680 0.10356 -0.0746 0.0118 0.9999
14.750 1.2226 0.11411 0.11109 -0.0781 0.0119 0.9999
15.000 1.2043 0.12213 0.11933 -0.0826 0.0121 0.9999
15.250 1.1867 0.13049 0.12787 -0.0879 0.0123 0.9999
15.500 1.1692 0.13963 0.13718 -0.0942 0.0124 0.9999
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