WORTMANN FX 05-H-126 AIRFOIL (fx05h126-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: WORTMANN FX 05-H-126 AIRFOIL (fx05h126-il) Reynolds number: 100,000 Max Cl/Cd: 24.34 at α=11° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx05h126-il-100000-n5.txt Download as CSV file: xf-fx05h126-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 05-H-126 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3695 0.10377 0.09850 -0.0039 0.6523 0.0585
-8.500 -0.3675 0.10041 0.09516 -0.0066 0.6513 0.0604
-8.250 -0.3717 0.09710 0.09189 -0.0110 0.6504 0.0623
-8.000 -0.3844 0.09385 0.08868 -0.0173 0.6495 0.0631
-7.750 -0.3902 0.09029 0.08505 -0.0225 0.6485 0.0635
-7.500 -0.3893 0.08655 0.08121 -0.0265 0.6470 0.0637
-7.250 -0.3843 0.08253 0.07710 -0.0291 0.6454 0.0638
-7.000 -0.3706 0.07697 0.07164 -0.0293 0.6438 0.0646
-6.750 -0.3587 0.07315 0.06779 -0.0301 0.6422 0.0652
-6.500 -0.3522 0.06412 0.05837 -0.0335 0.6411 0.0425
-6.250 -0.3361 0.06163 0.05589 -0.0334 0.6398 0.0405
-6.000 -0.3230 0.05800 0.05210 -0.0344 0.6386 0.0395
-5.750 -0.3085 0.05427 0.04810 -0.0352 0.6375 0.0395
-5.500 -0.2924 0.05073 0.04426 -0.0356 0.6364 0.0397
-5.250 -0.2751 0.04744 0.04065 -0.0357 0.6354 0.0391
-5.000 -0.2567 0.04418 0.03704 -0.0354 0.6344 0.0381
-4.750 -0.2368 0.04107 0.03349 -0.0349 0.6333 0.0372
-4.500 -0.2139 0.03831 0.03034 -0.0350 0.6313 0.0366
-4.250 -0.1902 0.03599 0.02758 -0.0348 0.6293 0.0363
-4.000 -0.1657 0.03406 0.02526 -0.0345 0.6275 0.0363
-3.750 -0.1404 0.03260 0.02349 -0.0344 0.6260 0.0370
-3.500 -0.1146 0.03148 0.02208 -0.0342 0.6246 0.0388
-3.250 -0.0881 0.03033 0.02061 -0.0340 0.6233 0.0400
-3.000 -0.0613 0.02920 0.01920 -0.0337 0.6221 0.0405
-2.750 -0.0343 0.02822 0.01801 -0.0334 0.6209 0.0410
-2.500 -0.0076 0.02739 0.01699 -0.0330 0.6198 0.0418
-2.250 0.0183 0.02661 0.01614 -0.0326 0.6187 0.0427
-2.000 0.0456 0.02637 0.01597 -0.0335 0.6160 0.0444
-1.750 0.0720 0.02630 0.01594 -0.0340 0.6139 0.0481
-1.500 0.0977 0.02620 0.01577 -0.0341 0.6118 0.0516
-1.250 0.1220 0.02594 0.01552 -0.0338 0.6098 0.0547
-1.000 0.1468 0.02578 0.01528 -0.0334 0.6080 0.0599
-0.750 0.1717 0.02559 0.01505 -0.0329 0.6066 0.0694
-0.500 0.1966 0.02522 0.01485 -0.0325 0.6054 0.1118
0.250 0.3740 0.02380 0.01572 -0.0526 0.5987 1.0000
0.500 0.3975 0.02433 0.01615 -0.0527 0.5956 1.0000
0.750 0.4206 0.02468 0.01637 -0.0522 0.5933 1.0000
1.000 0.4436 0.02494 0.01651 -0.0515 0.5915 1.0000
1.250 0.4668 0.02512 0.01657 -0.0506 0.5900 1.0000
1.500 0.4901 0.02529 0.01663 -0.0496 0.5888 1.0000
1.750 0.5108 0.02697 0.01837 -0.0515 0.5819 1.0000
2.000 0.5328 0.02752 0.01887 -0.0511 0.5790 1.0000
2.250 0.5556 0.02781 0.01910 -0.0504 0.5769 1.0000
2.500 0.5788 0.02801 0.01924 -0.0495 0.5753 1.0000
2.750 0.6025 0.02816 0.01932 -0.0486 0.5741 1.0000
3.250 0.6375 0.03070 0.02193 -0.0491 0.5627 1.0000
3.500 0.6606 0.03092 0.02214 -0.0483 0.5609 1.0000
3.750 0.6847 0.03101 0.02220 -0.0473 0.5595 1.0000
4.250 0.7133 0.03369 0.02499 -0.0470 0.5472 1.0000
4.500 0.7373 0.03379 0.02509 -0.0461 0.5456 1.0000
4.750 0.7627 0.03373 0.02503 -0.0451 0.5443 1.0000
5.250 0.7869 0.03643 0.02786 -0.0443 0.5311 1.0000
5.500 0.8131 0.03629 0.02775 -0.0434 0.5298 1.0000
6.000 0.8114 0.04067 0.03222 -0.0418 0.5098 1.0000
6.250 0.8273 0.04130 0.03289 -0.0407 0.5052 1.0000
6.500 0.8532 0.04123 0.03290 -0.0400 0.5030 1.0000
6.750 0.8799 0.04108 0.03282 -0.0393 0.5012 1.0000
7.000 0.8682 0.04338 0.03514 -0.0370 0.4899 1.0000
7.250 0.8889 0.04362 0.03546 -0.0361 0.4864 1.0000
7.500 0.8901 0.04516 0.03705 -0.0345 0.4768 1.0000
7.750 0.9124 0.04504 0.03703 -0.0336 0.4721 1.0000
8.000 0.9234 0.04568 0.03774 -0.0324 0.4630 1.0000
8.500 0.9633 0.04533 0.03757 -0.0303 0.4483 1.0000
9.000 0.9887 0.04631 0.03876 -0.0282 0.4282 1.0000
9.250 1.0144 0.04539 0.03795 -0.0272 0.4203 1.0000
9.500 1.0264 0.04601 0.03865 -0.0262 0.4078 1.0000
9.750 1.0420 0.04631 0.03904 -0.0252 0.3954 1.0000
10.000 1.0611 0.04630 0.03915 -0.0243 0.3831 1.0000
10.250 1.0816 0.04614 0.03907 -0.0233 0.3690 1.0000
10.500 1.1010 0.04603 0.03901 -0.0222 0.3510 1.0000
10.750 1.1177 0.04620 0.03917 -0.0211 0.3274 1.0000
11.000 1.1320 0.04650 0.03937 -0.0198 0.2945 1.0000
11.250 1.1395 0.04748 0.04010 -0.0184 0.2575 1.0000
11.500 1.1385 0.04958 0.04195 -0.0173 0.2221 1.0000
11.750 1.1348 0.05219 0.04433 -0.0164 0.1926 1.0000
12.000 1.1314 0.05493 0.04690 -0.0158 0.1689 1.0000
12.250 1.1300 0.05758 0.04944 -0.0152 0.1504 1.0000
12.500 1.1307 0.06008 0.05188 -0.0148 0.1354 1.0000
12.750 1.1334 0.06242 0.05420 -0.0144 0.1232 1.0000
13.000 1.1374 0.06463 0.05641 -0.0140 0.1136 1.0000
13.250 1.1407 0.06692 0.05867 -0.0136 0.1059 1.0000
13.500 1.1476 0.06885 0.06068 -0.0132 0.0990 1.0000
13.750 1.1517 0.07107 0.06286 -0.0129 0.0927 1.0000
14.000 1.1566 0.07336 0.06523 -0.0128 0.0855 1.0000
14.250 1.1590 0.07596 0.06783 -0.0128 0.0784 1.0000
14.500 1.1601 0.07889 0.07081 -0.0131 0.0714 1.0000
14.750 1.1626 0.08166 0.07367 -0.0134 0.0649 1.0000
15.000 1.1650 0.08449 0.07660 -0.0137 0.0598 1.0000
15.250 1.1668 0.08745 0.07963 -0.0141 0.0548 1.0000
15.500 1.1688 0.09048 0.08284 -0.0146 0.0497 1.0000
15.750 1.1669 0.09409 0.08646 -0.0154 0.0457 1.0000
16.000 1.1685 0.09726 0.08983 -0.0159 0.0406 1.0000
16.250 1.1659 0.10114 0.09376 -0.0169 0.0374 1.0000
16.500 1.1653 0.10469 0.09742 -0.0176 0.0335 1.0000
16.750 1.1628 0.10871 0.10153 -0.0189 0.0307 1.0000
17.000 1.1596 0.11280 0.10566 -0.0201 0.0288 1.0000
17.250 1.1588 0.11657 0.10960 -0.0211 0.0264 1.0000
17.500 1.1559 0.12082 0.11395 -0.0227 0.0248 1.0000
17.750 1.1529 0.12508 0.11829 -0.0243 0.0238 1.0000
18.000 1.1510 0.12915 0.12247 -0.0257 0.0228 1.0000
18.250 1.1494 0.13325 0.12676 -0.0272 0.0219 1.0000
18.500 1.1466 0.13769 0.13137 -0.0290 0.0212 1.0000
18.750 1.1422 0.14259 0.13645 -0.0312 0.0205 1.0000
19.000 1.1375 0.14765 0.14166 -0.0337 0.0201 1.0000
19.250 1.1321 0.15303 0.14718 -0.0365 0.0196 1.0000
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