FX 60-100 AIRFOIL (fx60100-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 60-100 AIRFOIL (fx60100-il) Reynolds number: 200,000 Max Cl/Cd: 84.89 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx60100-il-200000.txt Download as CSV file: xf-fx60100-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: FX 60-100 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3675 0.09834 0.09483 -0.0404 1.0000 0.0471
-9.000 -0.3767 0.09469 0.09127 -0.0437 1.0000 0.0475
-8.750 -0.3848 0.09121 0.08787 -0.0456 1.0000 0.0477
-8.500 -0.3724 0.08782 0.08449 -0.0410 1.0000 0.0493
-8.250 -0.3691 0.08584 0.08255 -0.0393 1.0000 0.0503
-8.000 -0.3725 0.08372 0.08049 -0.0379 1.0000 0.0513
-7.750 -0.3819 0.08186 0.07871 -0.0359 1.0000 0.0525
-7.500 -0.3988 0.08032 0.07726 -0.0330 1.0000 0.0531
-7.250 -0.4195 0.07904 0.07607 -0.0296 1.0000 0.0533
-7.000 -0.4347 0.07670 0.07381 -0.0286 1.0000 0.0543
-6.750 -0.4466 0.07337 0.07054 -0.0300 1.0000 0.0555
-6.500 -0.4350 0.05642 0.05312 -0.0615 0.9952 0.0597
-6.250 -0.4112 0.05425 0.05113 -0.0607 0.9922 0.0617
-6.000 -0.3783 0.04947 0.04619 -0.0681 0.9872 0.0665
-5.750 -0.3375 0.04237 0.03864 -0.0796 0.9834 0.0745
-5.500 -0.3030 0.03802 0.03385 -0.0859 0.9779 0.0857
-5.250 -0.2486 0.02548 0.01960 -0.0912 0.9770 0.0311
-5.000 -0.2068 0.02283 0.01617 -0.0934 0.9743 0.0277
-4.750 -0.1685 0.02047 0.01361 -0.0960 0.9720 0.0291
-4.500 -0.1296 0.01909 0.01212 -0.0983 0.9689 0.0307
-4.250 -0.0953 0.01775 0.01069 -0.0995 0.9635 0.0308
-4.000 -0.0556 0.01663 0.00951 -0.1018 0.9598 0.0317
-3.750 -0.0133 0.01571 0.00850 -0.1047 0.9572 0.0340
-3.500 0.0221 0.01496 0.00762 -0.1063 0.9521 0.0387
-3.250 0.0629 0.01293 0.00657 -0.1101 0.9487 0.2633
-3.000 0.1025 0.01261 0.00666 -0.1126 0.9449 0.4086
-2.750 0.1455 0.01267 0.00676 -0.1154 0.9421 0.4680
-2.500 0.1768 0.01266 0.00671 -0.1158 0.9343 0.4893
-2.250 0.2178 0.01255 0.00653 -0.1181 0.9302 0.5106
-2.000 0.2565 0.01245 0.00642 -0.1199 0.9264 0.5300
-1.750 0.2859 0.01244 0.00640 -0.1199 0.9183 0.5481
-1.500 0.3240 0.01227 0.00621 -0.1214 0.9140 0.5658
-1.250 0.3530 0.01217 0.00611 -0.1213 0.9049 0.5796
-1.000 0.3882 0.01194 0.00587 -0.1221 0.8993 0.5936
-0.750 0.4156 0.01186 0.00580 -0.1217 0.8898 0.6065
-0.500 0.4475 0.01167 0.00561 -0.1219 0.8833 0.6200
-0.250 0.4750 0.01153 0.00548 -0.1214 0.8729 0.6324
0.000 0.5029 0.01139 0.00535 -0.1210 0.8626 0.6445
0.250 0.5321 0.01122 0.00519 -0.1207 0.8538 0.6576
0.500 0.5592 0.01110 0.00509 -0.1201 0.8427 0.6719
0.750 0.5858 0.01098 0.00501 -0.1193 0.8304 0.6865
1.000 0.6125 0.01084 0.00490 -0.1186 0.8170 0.7013
1.250 0.6387 0.01069 0.00479 -0.1177 0.8024 0.7170
1.500 0.6649 0.01055 0.00468 -0.1168 0.7870 0.7341
1.750 0.6909 0.01042 0.00456 -0.1159 0.7703 0.7535
2.000 0.7160 0.01029 0.00449 -0.1149 0.7518 0.7756
2.250 0.7402 0.01018 0.00447 -0.1137 0.7333 0.8048
2.500 0.7620 0.01000 0.00439 -0.1119 0.7151 0.8519
2.750 0.7867 0.00981 0.00426 -0.1107 0.6955 1.0000
3.000 0.8151 0.00995 0.00430 -0.1108 0.6719 1.0000
3.250 0.8425 0.01013 0.00436 -0.1105 0.6478 1.0000
3.500 0.8693 0.01035 0.00446 -0.1102 0.6240 1.0000
3.750 0.8957 0.01059 0.00461 -0.1098 0.5999 1.0000
4.000 0.9217 0.01086 0.00481 -0.1094 0.5763 1.0000
4.250 0.9474 0.01116 0.00502 -0.1088 0.5528 1.0000
4.500 0.9728 0.01147 0.00527 -0.1083 0.5278 1.0000
4.750 0.9977 0.01181 0.00553 -0.1077 0.5008 1.0000
5.000 1.0223 0.01217 0.00584 -0.1071 0.4736 1.0000
5.250 1.0464 0.01256 0.00617 -0.1064 0.4441 1.0000
5.500 1.0695 0.01303 0.00651 -0.1055 0.4102 1.0000
5.750 1.0916 0.01357 0.00691 -0.1046 0.3689 1.0000
6.000 1.1122 0.01425 0.00739 -0.1035 0.3221 1.0000
6.250 1.1321 0.01504 0.00794 -0.1024 0.2730 1.0000
6.500 1.1516 0.01591 0.00858 -0.1012 0.2269 1.0000
6.750 1.1709 0.01685 0.00932 -0.1001 0.1880 1.0000
7.000 1.1898 0.01783 0.01015 -0.0989 0.1588 1.0000
7.250 1.2081 0.01887 0.01106 -0.0976 0.1362 1.0000
7.500 1.2265 0.01990 0.01204 -0.0963 0.1184 1.0000
7.750 1.2453 0.02086 0.01298 -0.0950 0.1045 1.0000
8.000 1.2628 0.02192 0.01401 -0.0936 0.0940 1.0000
8.250 1.2775 0.02336 0.01535 -0.0918 0.0857 1.0000
8.500 1.2970 0.02424 0.01639 -0.0906 0.0794 1.0000
8.750 1.3134 0.02556 0.01768 -0.0891 0.0746 1.0000
9.000 1.3319 0.02668 0.01895 -0.0877 0.0705 1.0000
9.250 1.3496 0.02748 0.01983 -0.0864 0.0661 1.0000
9.500 1.3652 0.02887 0.02119 -0.0851 0.0619 1.0000
9.750 1.3807 0.02959 0.02211 -0.0834 0.0582 1.0000
10.000 1.3927 0.03039 0.02297 -0.0815 0.0542 1.0000
10.250 1.4047 0.03212 0.02472 -0.0799 0.0503 1.0000
10.500 1.4155 0.03272 0.02556 -0.0777 0.0474 1.0000
10.750 1.4254 0.03354 0.02654 -0.0758 0.0439 1.0000
11.000 1.4316 0.03490 0.02794 -0.0738 0.0404 1.0000
11.250 1.4411 0.03584 0.02916 -0.0721 0.0359 1.0000
11.500 1.4436 0.03744 0.03080 -0.0702 0.0295 1.0000
11.750 1.4456 0.03945 0.03292 -0.0685 0.0230 1.0000
12.000 1.4435 0.04228 0.03593 -0.0665 0.0199 1.0000
12.250 1.4470 0.04439 0.03817 -0.0654 0.0175 1.0000
12.500 1.4450 0.04718 0.04105 -0.0644 0.0160 1.0000
12.750 1.4374 0.05094 0.04495 -0.0634 0.0151 1.0000
13.000 1.4358 0.05421 0.04845 -0.0628 0.0144 1.0000
13.250 1.4318 0.05789 0.05234 -0.0625 0.0139 1.0000
13.500 1.4265 0.06191 0.05656 -0.0626 0.0134 1.0000
13.750 1.4199 0.06626 0.06111 -0.0632 0.0130 1.0000
14.000 1.4121 0.07095 0.06600 -0.0641 0.0127 1.0000
14.250 1.4032 0.07601 0.07126 -0.0656 0.0124 1.0000
14.500 1.3931 0.08155 0.07699 -0.0675 0.0122 1.0000
14.750 1.3817 0.08754 0.08318 -0.0698 0.0121 1.0000
15.000 1.3693 0.09403 0.08987 -0.0728 0.0120 1.0000
15.250 1.3552 0.10115 0.09720 -0.0763 0.0119 1.0000
15.500 1.3399 0.10882 0.10508 -0.0804 0.0119 1.0000
15.750 1.3218 0.11755 0.11404 -0.0854 0.0120 1.0000
16.000 1.3009 0.12742 0.12416 -0.0915 0.0122 1.0000
16.250 1.2773 0.13854 0.13551 -0.0986 0.0124 1.0000
16.500 1.2467 0.15258 0.14980 -0.1080 0.0129 1.0000
16.750 1.2064 0.17104 0.16845 -0.1202 0.0139 1.0000
17.000 1.1556 0.19620 0.19364 -0.1353 0.0158 1.0000
17.250 1.1167 0.22505 0.22224 -0.1494 0.0202 1.0000
17.500 1.1202 0.23133 0.22849 -0.1529 0.0202 1.0000
17.750 1.1248 0.23716 0.23431 -0.1562 0.0204 1.0000
18.000 1.1309 0.24175 0.23889 -0.1585 0.0210 1.0000
18.250 0.8867 0.24217 0.23991 -0.1377 0.0392 1.0000
18.500 0.8792 0.24729 0.24499 -0.1422 0.0372 1.0000
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