FX 61-140 AIRFOIL (fx61140-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 61-140 AIRFOIL (fx61140-il) Reynolds number: 100,000 Max Cl/Cd: 51.64 at α=9.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx61140-il-100000.txt Download as CSV file: xf-fx61140-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: FX 61-140 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4426 0.09888 0.09437 -0.0461 1.0000 0.1215
-9.250 -0.3961 0.09691 0.09229 -0.0382 1.0000 0.1274
-9.000 -0.4179 0.09287 0.08839 -0.0418 1.0000 0.1345
-8.750 -0.4120 0.08937 0.08494 -0.0404 1.0000 0.1395
-8.500 -0.4165 0.08630 0.08195 -0.0405 1.0000 0.1468
-8.250 -0.4724 0.08126 0.07710 -0.0451 1.0000 0.1491
-8.000 -0.4343 0.07951 0.07535 -0.0403 1.0000 0.1596
-6.000 -0.5269 0.04092 0.03449 -0.0455 1.0000 0.0642
-5.750 -0.5039 0.03693 0.02967 -0.0455 1.0000 0.0541
-5.500 -0.4607 0.03429 0.02655 -0.0490 0.9950 0.0536
-5.250 -0.4169 0.03059 0.02251 -0.0527 0.9884 0.0549
-5.000 -0.3717 0.02818 0.01981 -0.0554 0.9809 0.0548
-4.750 -0.3274 0.02606 0.01765 -0.0581 0.9736 0.0572
-4.500 -0.2849 0.02469 0.01618 -0.0605 0.9632 0.0646
-4.250 -0.2455 0.02295 0.01463 -0.0626 0.9532 0.0740
-4.000 -0.1989 0.02117 0.01301 -0.0666 0.9442 0.1010
-3.750 -0.1639 0.01959 0.01421 -0.0667 0.9345 0.6280
-3.500 -0.1403 0.02177 0.01627 -0.0612 0.9201 0.6701
-3.250 -0.1265 0.02405 0.01851 -0.0524 0.9064 0.7025
-3.000 -0.1095 0.02562 0.01999 -0.0448 0.8939 0.7325
-2.750 -0.0754 0.02579 0.01996 -0.0439 0.8831 0.7534
-2.500 -0.0249 0.02540 0.01930 -0.0472 0.8766 0.7667
-2.250 0.0120 0.02502 0.01873 -0.0476 0.8645 0.7752
-2.000 0.0515 0.02453 0.01805 -0.0495 0.8521 0.7851
-1.750 0.0907 0.02406 0.01738 -0.0520 0.8391 0.7953
-1.500 0.1298 0.02362 0.01676 -0.0534 0.8262 0.8022
-1.250 0.1636 0.02324 0.01620 -0.0550 0.8121 0.8106
-1.000 0.1973 0.02290 0.01572 -0.0559 0.7984 0.8174
-0.750 0.2257 0.02263 0.01529 -0.0565 0.7847 0.8249
-0.500 0.2559 0.02237 0.01489 -0.0569 0.7717 0.8311
-0.250 0.2825 0.02218 0.01456 -0.0573 0.7593 0.8381
0.000 0.3101 0.02195 0.01422 -0.0572 0.7472 0.8437
0.250 0.3309 0.02187 0.01406 -0.0567 0.7346 0.8506
0.500 0.3548 0.02168 0.01381 -0.0560 0.7231 0.8559
0.750 0.3787 0.02160 0.01365 -0.0558 0.7124 0.8619
1.000 0.4068 0.02147 0.01340 -0.0562 0.7030 0.8673
1.250 0.4273 0.02139 0.01332 -0.0552 0.6920 0.8726
1.500 0.4489 0.02142 0.01331 -0.0548 0.6821 0.8783
1.750 0.4786 0.02129 0.01309 -0.0552 0.6739 0.8828
2.000 0.4975 0.02131 0.01315 -0.0541 0.6637 0.8879
2.250 0.5208 0.02140 0.01321 -0.0540 0.6549 0.8932
2.500 0.5473 0.02132 0.01311 -0.0539 0.6467 0.8975
2.750 0.5675 0.02143 0.01328 -0.0531 0.6376 0.9026
3.250 0.6157 0.02157 0.01343 -0.0526 0.6210 0.9119
3.500 0.6421 0.02167 0.01353 -0.0528 0.6135 0.9168
3.750 0.6648 0.02183 0.01376 -0.0524 0.6049 0.9215
4.000 0.6885 0.02197 0.01395 -0.0521 0.5971 0.9261
4.250 0.7144 0.02210 0.01411 -0.0522 0.5893 0.9310
4.500 0.7357 0.02237 0.01448 -0.0517 0.5811 0.9358
4.750 0.7650 0.02247 0.01462 -0.0522 0.5739 0.9403
5.000 0.7844 0.02284 0.01513 -0.0515 0.5655 0.9458
5.250 0.8161 0.02296 0.01526 -0.0524 0.5588 0.9503
5.500 0.8356 0.02340 0.01588 -0.0518 0.5500 0.9558
5.750 0.8698 0.02353 0.01603 -0.0531 0.5435 0.9606
6.000 0.8911 0.02404 0.01677 -0.0529 0.5340 0.9666
6.250 0.9216 0.02436 0.01719 -0.0539 0.5263 0.9721
6.500 0.9543 0.02472 0.01769 -0.0555 0.5174 0.9777
6.750 0.9834 0.02529 0.01849 -0.0566 0.5083 0.9848
7.000 1.0264 0.02542 0.01867 -0.0596 0.5004 0.9911
7.250 1.0441 0.02607 0.01956 -0.0589 0.4900 1.0000
7.500 1.0696 0.02646 0.02009 -0.0591 0.4800 1.0000
7.750 1.1030 0.02641 0.02011 -0.0602 0.4693 1.0000
8.000 1.1363 0.02618 0.01997 -0.0611 0.4565 1.0000
8.250 1.1641 0.02599 0.01991 -0.0613 0.4413 1.0000
8.500 1.1882 0.02559 0.01966 -0.0609 0.4222 1.0000
8.750 1.2160 0.02495 0.01907 -0.0608 0.4022 1.0000
9.000 1.2410 0.02474 0.01898 -0.0606 0.3835 1.0000
9.250 1.2602 0.02468 0.01920 -0.0597 0.3610 1.0000
9.500 1.2765 0.02472 0.01942 -0.0583 0.3336 1.0000
9.750 1.2860 0.02512 0.01991 -0.0562 0.2939 1.0000
10.000 1.2779 0.02660 0.02111 -0.0522 0.2238 1.0000
10.250 1.2569 0.02988 0.02379 -0.0483 0.1564 1.0000
10.500 1.2375 0.03374 0.02729 -0.0458 0.1232 1.0000
10.750 1.2239 0.03765 0.03106 -0.0446 0.1028 1.0000
11.000 1.2144 0.04156 0.03490 -0.0444 0.0878 1.0000
11.250 1.2074 0.04551 0.03882 -0.0448 0.0749 1.0000
11.500 1.2018 0.04948 0.04279 -0.0453 0.0645 1.0000
11.750 1.1979 0.05332 0.04657 -0.0453 0.0561 1.0000
12.000 1.1981 0.05682 0.05002 -0.0454 0.0481 1.0000
12.250 1.2053 0.05978 0.05307 -0.0450 0.0416 1.0000
12.500 1.2266 0.06184 0.05491 -0.0429 0.0360 1.0000
12.750 1.2425 0.06459 0.05795 -0.0425 0.0340 1.0000
13.000 1.2585 0.06772 0.06134 -0.0420 0.0325 1.0000
13.250 1.2680 0.07149 0.06543 -0.0420 0.0316 1.0000
13.500 1.2703 0.07585 0.07010 -0.0424 0.0311 1.0000
13.750 1.2664 0.08074 0.07529 -0.0434 0.0309 1.0000
14.000 1.2570 0.08619 0.08106 -0.0450 0.0309 1.0000
14.250 1.2437 0.09213 0.08731 -0.0473 0.0311 1.0000
14.500 1.2277 0.09854 0.09401 -0.0503 0.0313 1.0000
14.750 1.2090 0.10561 0.10136 -0.0540 0.0315 1.0000
15.000 1.1898 0.11313 0.10914 -0.0585 0.0320 1.0000
15.250 1.1688 0.12140 0.11765 -0.0638 0.0324 1.0000
15.500 1.1472 0.13039 0.12685 -0.0700 0.0329 1.0000
15.750 1.1258 0.14000 0.13664 -0.0769 0.0334 1.0000
16.000 1.1046 0.15040 0.14714 -0.0845 0.0341 1.0000
16.250 1.0828 0.16196 0.15879 -0.0927 0.0349 1.0000
16.500 1.0697 0.17198 0.16883 -0.0993 0.0356 1.0000
16.750 1.0245 0.20026 0.19704 -0.1165 0.0440 1.0000
17.000 1.0320 0.20526 0.20203 -0.1189 0.0458 1.0000
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