I.S.A. 571 (isa571-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: I.S.A. 571 (isa571-il) Reynolds number: 100,000 Max Cl/Cd: 51.58 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-isa571-il-100000.txt Download as CSV file: xf-isa571-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: I.S.A. 571
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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4030 0.09571 0.09087 -0.0186 1.0000 0.0675
-8.000 -0.4096 0.09360 0.08886 -0.0197 1.0000 0.0691
-7.750 -0.4128 0.09140 0.08673 -0.0265 1.0000 0.0703
-7.500 -0.4097 0.08884 0.08410 -0.0346 1.0000 0.0708
-7.250 -0.4029 0.08357 0.07899 -0.0229 1.0000 0.0739
-7.000 -0.3972 0.08063 0.07608 -0.0232 1.0000 0.0777
-6.750 -0.3869 0.07776 0.07313 -0.0321 1.0000 0.0825
-6.500 -0.3794 0.07328 0.06864 -0.0338 1.0000 0.0841
-6.250 -0.3736 0.06993 0.06539 -0.0301 1.0000 0.0864
-6.000 -0.3629 0.06683 0.06227 -0.0304 1.0000 0.0906
-5.750 -0.3397 0.06289 0.05802 -0.0383 1.0000 0.0970
-5.500 -0.3324 0.05928 0.05456 -0.0354 1.0000 0.0995
-5.250 -0.3153 0.05628 0.05145 -0.0364 1.0000 0.1065
-5.000 -0.2959 0.05238 0.04739 -0.0387 1.0000 0.1124
-4.750 -0.2728 0.04940 0.04415 -0.0410 1.0000 0.1244
-4.500 -0.2531 0.04661 0.04122 -0.0417 1.0000 0.1383
-4.250 -0.2375 0.04358 0.03828 -0.0406 1.0000 0.1471
-4.000 -0.2122 0.04092 0.03531 -0.0425 1.0000 0.1673
-3.750 -0.1919 0.03804 0.03240 -0.0424 1.0000 0.1832
-3.500 -0.1716 0.03571 0.03001 -0.0423 1.0000 0.2123
-3.000 -0.0965 0.02935 0.02247 -0.0461 1.0000 0.1681
-2.750 -0.0839 0.02818 0.02174 -0.0453 1.0000 0.2428
-2.500 -0.0191 0.02366 0.01501 -0.0469 1.0000 0.1097
-2.250 0.0091 0.02203 0.01338 -0.0474 1.0000 0.1160
-2.000 0.0376 0.02106 0.01213 -0.0474 1.0000 0.1192
-1.750 0.0648 0.02026 0.01117 -0.0475 1.0000 0.1259
-1.500 0.0913 0.01959 0.01048 -0.0475 1.0000 0.1297
-1.250 0.1170 0.01916 0.00999 -0.0474 1.0000 0.1345
-1.000 0.1458 0.01870 0.00961 -0.0481 0.9988 0.1435
-0.750 0.1987 0.01802 0.00907 -0.0532 0.9892 0.1604
-0.500 0.2516 0.01722 0.00849 -0.0582 0.9785 0.2041
-0.250 0.2957 0.01479 0.00802 -0.0606 0.9678 1.0000
0.000 0.3455 0.01471 0.00773 -0.0648 0.9502 1.0000
0.250 0.3954 0.01447 0.00736 -0.0688 0.9325 1.0000
0.500 0.4458 0.01405 0.00688 -0.0725 0.9146 1.0000
0.750 0.4875 0.01359 0.00637 -0.0743 0.8898 1.0000
1.000 0.5290 0.01310 0.00584 -0.0759 0.8597 1.0000
1.250 0.5690 0.01267 0.00529 -0.0769 0.8167 1.0000
1.500 0.6055 0.01252 0.00488 -0.0773 0.7606 1.0000
1.750 0.6357 0.01276 0.00478 -0.0768 0.7035 1.0000
2.000 0.6619 0.01323 0.00489 -0.0758 0.6559 1.0000
2.250 0.6869 0.01372 0.00512 -0.0749 0.6175 1.0000
2.500 0.7122 0.01421 0.00540 -0.0742 0.5875 1.0000
2.750 0.7377 0.01467 0.00576 -0.0737 0.5627 1.0000
3.000 0.7634 0.01513 0.00607 -0.0731 0.5420 1.0000
3.250 0.7889 0.01557 0.00644 -0.0726 0.5223 1.0000
3.500 0.8145 0.01601 0.00683 -0.0721 0.5043 1.0000
3.750 0.8399 0.01647 0.00725 -0.0716 0.4871 1.0000
4.000 0.8653 0.01695 0.00765 -0.0711 0.4702 1.0000
4.250 0.8902 0.01743 0.00811 -0.0706 0.4528 1.0000
4.500 0.9148 0.01792 0.00861 -0.0699 0.4348 1.0000
4.750 0.9394 0.01844 0.00915 -0.0693 0.4173 1.0000
5.000 0.9640 0.01899 0.00969 -0.0687 0.4001 1.0000
5.250 0.9885 0.01959 0.01026 -0.0682 0.3832 1.0000
5.500 1.0123 0.02017 0.01091 -0.0675 0.3653 1.0000
5.750 1.0362 0.02079 0.01162 -0.0668 0.3482 1.0000
6.000 1.0601 0.02145 0.01239 -0.0661 0.3320 1.0000
6.250 1.0836 0.02207 0.01311 -0.0653 0.3160 1.0000
6.500 1.1056 0.02242 0.01348 -0.0643 0.2979 1.0000
6.750 1.1252 0.02250 0.01369 -0.0629 0.2761 1.0000
7.000 1.1454 0.02265 0.01399 -0.0616 0.2562 1.0000
7.250 1.1650 0.02278 0.01428 -0.0603 0.2345 1.0000
7.500 1.1838 0.02295 0.01454 -0.0590 0.2082 1.0000
7.750 1.2010 0.02351 0.01509 -0.0575 0.1725 1.0000
8.000 1.2122 0.02530 0.01647 -0.0553 0.0942 1.0000
8.250 1.2175 0.02789 0.01879 -0.0523 0.0671 1.0000
8.500 1.2291 0.02961 0.02065 -0.0498 0.0572 1.0000
8.750 1.2383 0.03146 0.02257 -0.0472 0.0526 1.0000
9.000 1.2491 0.03320 0.02444 -0.0447 0.0492 1.0000
9.250 1.2583 0.03505 0.02631 -0.0424 0.0462 1.0000
9.500 1.2677 0.03733 0.02865 -0.0401 0.0437 1.0000
9.750 1.2803 0.03942 0.03095 -0.0381 0.0416 1.0000
10.000 1.2943 0.04194 0.03366 -0.0364 0.0405 1.0000
10.250 1.3078 0.04478 0.03674 -0.0347 0.0397 1.0000
10.500 1.3184 0.04793 0.04018 -0.0329 0.0392 1.0000
10.750 1.3235 0.05129 0.04390 -0.0306 0.0391 1.0000
11.000 1.3204 0.05477 0.04775 -0.0276 0.0392 1.0000
11.250 1.3106 0.05835 0.05169 -0.0246 0.0394 1.0000
11.500 1.2963 0.06214 0.05582 -0.0221 0.0396 1.0000
11.750 1.2787 0.06632 0.06031 -0.0205 0.0398 1.0000
12.000 1.2583 0.07109 0.06538 -0.0202 0.0401 1.0000
12.250 1.2358 0.07661 0.07117 -0.0213 0.0404 1.0000
12.500 1.2118 0.08304 0.07785 -0.0241 0.0409 1.0000
12.750 1.1865 0.09046 0.08549 -0.0283 0.0413 1.0000
13.000 1.1598 0.09895 0.09414 -0.0338 0.0418 1.0000
13.250 1.1315 0.10867 0.10400 -0.0405 0.0423 1.0000
13.500 1.1023 0.11952 0.11496 -0.0479 0.0430 1.0000
13.750 1.0754 0.13072 0.12621 -0.0549 0.0437 1.0000
14.000 1.0572 0.14042 0.13591 -0.0601 0.0444 1.0000
14.250 0.9967 0.16967 0.16497 -0.0774 0.0524 1.0000
14.500 1.0000 0.17457 0.16990 -0.0788 0.0539 1.0000
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Polar data table (+)
Polar graphs
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