FX 73-K-170/22 (fx73k170-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 73-K-170/22 (fx73k170-il) Reynolds number: 200,000 Max Cl/Cd: 62.98 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx73k170-il-200000.txt Download as CSV file: xf-fx73k170-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: FX 73-K-170/22
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
------ -------- --------- --------- -------- -------- --------
-13.250 0.0614 0.10247 0.09846 -0.1362 0.8882 0.0518
-13.000 -0.0501 0.11190 0.10775 -0.1388 0.9047 0.0488
-12.750 -0.0313 0.10971 0.10554 -0.1381 0.9017 0.0501
-12.500 -0.0195 0.10683 0.10264 -0.1395 0.8985 0.0514
-12.250 -0.0093 0.10380 0.09959 -0.1417 0.8957 0.0531
-12.000 -0.0045 0.09986 0.09564 -0.1451 0.8930 0.0565
-11.750 -0.0158 0.09417 0.08997 -0.1533 0.8900 0.0589
-11.500 -0.0252 0.08832 0.08419 -0.1563 0.8868 0.0600
-11.250 -0.0079 0.08663 0.08247 -0.1547 0.8837 0.0610
-11.000 0.0049 0.08441 0.08023 -0.1549 0.8809 0.0623
-10.750 0.0153 0.08194 0.07775 -0.1561 0.8781 0.0649
-10.500 0.0194 0.07830 0.07409 -0.1590 0.8754 0.0661
-8.000 -0.1911 0.03756 0.03164 -0.1503 0.8305 0.0360
-7.750 -0.1921 0.03527 0.02906 -0.1467 0.8257 0.0338
-7.500 -0.1855 0.03333 0.02680 -0.1440 0.8211 0.0335
-7.250 -0.1690 0.03169 0.02487 -0.1427 0.8182 0.0336
-7.000 -0.1473 0.03037 0.02332 -0.1421 0.8161 0.0348
-6.750 -0.1238 0.02872 0.02138 -0.1415 0.8144 0.0345
-6.500 -0.1226 0.02839 0.02100 -0.1373 0.8076 0.0346
-6.250 -0.1018 0.02730 0.01976 -0.1361 0.8044 0.0351
-6.000 -0.0767 0.02624 0.01858 -0.1356 0.8022 0.0363
-5.750 -0.0503 0.02536 0.01759 -0.1353 0.8005 0.0378
-5.500 -0.0408 0.02519 0.01740 -0.1324 0.7962 0.0387
-5.250 -0.0377 0.02487 0.01718 -0.1288 0.7902 0.0424
-5.000 -0.0148 0.02436 0.01662 -0.1282 0.7876 0.0470
-4.750 0.0080 0.02338 0.01566 -0.1277 0.7858 0.0542
-4.500 0.0327 0.02244 0.01472 -0.1275 0.7843 0.0749
-4.250 0.0158 0.02329 0.01568 -0.1208 0.7749 0.0879
-4.000 0.0256 0.02145 0.01492 -0.1192 0.7720 0.3002
-3.750 0.0437 0.02074 0.01511 -0.1173 0.7703 0.5219
-3.500 0.0342 0.02197 0.01638 -0.1114 0.7626 0.5528
-3.250 0.0496 0.02265 0.01704 -0.1089 0.7584 0.5889
-3.000 0.0782 0.02308 0.01735 -0.1085 0.7565 0.6166
-2.750 0.1113 0.02334 0.01756 -0.1087 0.7553 0.6343
-2.500 0.0822 0.02482 0.01908 -0.0997 0.7449 0.6379
-2.250 0.1084 0.02519 0.01940 -0.0989 0.7425 0.6536
-2.000 0.1381 0.02551 0.01969 -0.0986 0.7410 0.6698
-1.750 0.1709 0.02573 0.01988 -0.0987 0.7400 0.6852
-1.500 0.1314 0.02752 0.02170 -0.0886 0.7283 0.6899
-1.250 0.1607 0.02755 0.02166 -0.0885 0.7266 0.6999
-1.000 0.1927 0.02748 0.02150 -0.0890 0.7254 0.7086
-0.750 0.1958 0.02833 0.02232 -0.0854 0.7200 0.7146
-0.500 0.2485 0.02752 0.02141 -0.0889 0.7216 0.7209
-0.250 0.2962 0.02697 0.02073 -0.0922 0.7224 0.7273
0.000 0.3444 0.02642 0.02013 -0.0953 0.7229 0.7316
0.250 0.2389 0.03061 0.02443 -0.0763 0.7002 0.7362
0.500 0.2664 0.03063 0.02435 -0.0765 0.6978 0.7419
0.750 0.2978 0.03044 0.02412 -0.0770 0.6964 0.7455
1.000 0.3318 0.03018 0.02382 -0.0779 0.6953 0.7498
1.250 0.3676 0.02988 0.02345 -0.0791 0.6945 0.7543
1.500 0.4065 0.02942 0.02293 -0.0808 0.6939 0.7584
1.750 0.3788 0.03147 0.02501 -0.0736 0.6815 0.7620
2.000 0.4126 0.03124 0.02475 -0.0745 0.6804 0.7659
2.250 0.4500 0.03082 0.02429 -0.0759 0.6797 0.7697
2.500 0.4865 0.03050 0.02393 -0.0773 0.6791 0.7737
2.750 0.4641 0.03254 0.02600 -0.0713 0.6666 0.7774
3.000 0.4998 0.03219 0.02565 -0.0724 0.6657 0.7808
3.250 0.5383 0.03166 0.02511 -0.0739 0.6650 0.7848
3.500 0.5743 0.03130 0.02473 -0.0751 0.6641 0.7889
3.750 0.5581 0.03337 0.02684 -0.0703 0.6517 0.7926
4.000 0.5557 0.03504 0.02855 -0.0675 0.6418 0.7966
4.250 0.5878 0.03488 0.02839 -0.0684 0.6393 0.8010
4.500 0.6239 0.03447 0.02800 -0.0697 0.6379 0.8055
4.750 0.6615 0.03403 0.02762 -0.0712 0.6369 0.8093
5.000 0.7012 0.03342 0.02704 -0.0728 0.6362 0.8138
5.250 0.7415 0.03267 0.02632 -0.0745 0.6357 0.8190
5.500 0.7828 0.03188 0.02561 -0.0763 0.6352 0.8235
5.750 0.8247 0.03099 0.02479 -0.0782 0.6349 0.8287
6.250 0.8169 0.03546 0.02940 -0.0738 0.6098 0.8412
6.500 0.8574 0.03471 0.02874 -0.0756 0.6089 0.8488
6.750 0.9028 0.03371 0.02784 -0.0780 0.6084 0.8562
7.000 0.9497 0.03240 0.02664 -0.0805 0.6081 0.8653
7.250 1.0005 0.03100 0.02539 -0.0836 0.6081 0.8752
7.500 1.0567 0.02930 0.02385 -0.0874 0.6082 0.8881
7.750 1.1239 0.02717 0.02190 -0.0928 0.6085 0.9075
8.000 1.2054 0.02472 0.01968 -0.1007 0.6085 0.9609
8.250 1.2652 0.02274 0.01774 -0.1044 0.6068 1.0000
8.500 1.2679 0.02375 0.01881 -0.1018 0.5960 1.0000
8.750 1.3384 0.02125 0.01633 -0.1070 0.5911 1.0000
9.000 1.3406 0.02196 0.01710 -0.1038 0.5787 1.0000
9.250 1.3556 0.02197 0.01712 -0.1021 0.5642 1.0000
9.500 1.3666 0.02244 0.01762 -0.1002 0.5497 1.0000
9.750 1.3776 0.02301 0.01822 -0.0984 0.5341 1.0000
10.000 1.3908 0.02357 0.01879 -0.0969 0.5179 1.0000
10.250 1.4042 0.02418 0.01940 -0.0954 0.5009 1.0000
10.500 1.4084 0.02540 0.02062 -0.0931 0.4803 1.0000
10.750 1.4158 0.02644 0.02160 -0.0911 0.4575 1.0000
11.000 1.4189 0.02783 0.02293 -0.0888 0.4322 1.0000
11.250 1.4197 0.02940 0.02440 -0.0863 0.4045 1.0000
11.500 1.4159 0.03136 0.02622 -0.0836 0.3741 1.0000
11.750 1.4090 0.03368 0.02838 -0.0807 0.3422 1.0000
12.000 1.4007 0.03626 0.03080 -0.0781 0.3104 1.0000
12.250 1.3909 0.03915 0.03351 -0.0755 0.2783 1.0000
12.500 1.3785 0.04240 0.03657 -0.0731 0.2448 1.0000
12.750 1.3668 0.04577 0.03976 -0.0709 0.2117 1.0000
13.000 1.3544 0.04935 0.04313 -0.0689 0.1782 1.0000
13.250 1.3410 0.05315 0.04671 -0.0671 0.1455 1.0000
13.500 1.3274 0.05711 0.05046 -0.0654 0.1161 1.0000
13.750 1.3163 0.06092 0.05409 -0.0640 0.0924 1.0000
14.000 1.3074 0.06462 0.05767 -0.0628 0.0779 1.0000
14.250 1.3020 0.06805 0.06107 -0.0619 0.0672 1.0000
14.500 1.3002 0.07114 0.06421 -0.0611 0.0601 1.0000
14.750 1.2930 0.07483 0.06783 -0.0603 0.0547 1.0000
15.000 1.2964 0.07743 0.07055 -0.0599 0.0493 1.0000
15.250 1.2930 0.08075 0.07387 -0.0593 0.0459 1.0000
15.500 1.2928 0.08374 0.07694 -0.0587 0.0419 1.0000
15.750 1.2944 0.08658 0.07984 -0.0584 0.0389 1.0000
16.000 1.2918 0.08952 0.08269 -0.0575 0.0357 1.0000
16.250 1.2961 0.09216 0.08551 -0.0574 0.0333 1.0000
16.500 1.2990 0.09490 0.08831 -0.0574 0.0310 1.0000
16.750 1.3020 0.09703 0.09036 -0.0564 0.0286 1.0000
17.000 1.3070 0.09946 0.09294 -0.0562 0.0270 1.0000
17.250 1.3112 0.10204 0.09565 -0.0561 0.0253 1.0000
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