RAE(NPL) 5212 AIRFOIL (rae5212-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: RAE(NPL) 5212 AIRFOIL (rae5212-il) Reynolds number: 200,000 Max Cl/Cd: 57.8 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rae5212-il-200000.txt Download as CSV file: xf-rae5212-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: RAE(NPL) 5212 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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4945 0.08860 0.08489 -0.0456 1.0000 0.0664
-9.750 -0.5438 0.07855 0.07484 -0.0551 1.0000 0.0674
-9.500 -0.5714 0.07449 0.07077 -0.0558 1.0000 0.0674
-9.250 -0.6015 0.07181 0.06808 -0.0537 1.0000 0.0673
-9.000 -0.6381 0.06954 0.06569 -0.0507 1.0000 0.0677
-8.750 -0.6688 0.06800 0.06390 -0.0471 1.0000 0.0681
-8.500 -0.6849 0.06636 0.06203 -0.0439 1.0000 0.0683
-8.250 -0.6781 0.05860 0.05453 -0.0439 1.0000 0.0701
-8.000 -0.6742 0.05622 0.05219 -0.0419 1.0000 0.0712
-7.750 -0.6730 0.05404 0.04999 -0.0397 1.0000 0.0726
-7.500 -0.6735 0.05176 0.04759 -0.0376 1.0000 0.0747
-7.000 -0.6847 0.03674 0.03087 -0.0322 1.0000 0.0498
-6.750 -0.6621 0.03267 0.02636 -0.0320 0.9984 0.0448
-6.500 -0.6321 0.02886 0.02197 -0.0332 0.9954 0.0431
-6.250 -0.5998 0.02665 0.01943 -0.0344 0.9924 0.0434
-6.000 -0.5671 0.02532 0.01787 -0.0358 0.9886 0.0455
-5.750 -0.5327 0.02396 0.01624 -0.0371 0.9855 0.0468
-5.500 -0.4986 0.02296 0.01499 -0.0384 0.9824 0.0480
-5.250 -0.4700 0.02121 0.01328 -0.0389 0.9786 0.0501
-5.000 -0.4358 0.02050 0.01259 -0.0405 0.9748 0.0538
-4.750 -0.3985 0.01990 0.01189 -0.0424 0.9722 0.0571
-4.500 -0.3738 0.01877 0.01086 -0.0423 0.9666 0.0611
-4.250 -0.3400 0.01822 0.01030 -0.0437 0.9625 0.0671
-4.000 -0.3045 0.01735 0.00951 -0.0457 0.9597 0.0752
-3.750 -0.2794 0.01671 0.00891 -0.0456 0.9533 0.0865
-3.500 -0.2472 0.01588 0.00825 -0.0469 0.9490 0.1188
-3.250 -0.2223 0.01365 0.00796 -0.0480 0.9459 0.5233
-3.000 -0.1983 0.01387 0.00822 -0.0469 0.9389 0.5868
-2.750 -0.1652 0.01414 0.00846 -0.0475 0.9343 0.6191
-2.500 -0.1282 0.01440 0.00874 -0.0488 0.9315 0.6421
-2.250 -0.1048 0.01465 0.00898 -0.0476 0.9245 0.6595
-2.000 -0.0730 0.01488 0.00922 -0.0478 0.9200 0.6794
-1.750 -0.0385 0.01515 0.00955 -0.0482 0.9171 0.7028
-1.500 -0.0141 0.01531 0.00972 -0.0472 0.9108 0.7176
-1.250 0.0170 0.01527 0.00969 -0.0475 0.9060 0.7251
-1.000 0.0559 0.01513 0.00947 -0.0498 0.9031 0.7311
-0.750 0.0970 0.01492 0.00925 -0.0523 0.9012 0.7354
-0.500 0.1190 0.01493 0.00925 -0.0512 0.8932 0.7400
-0.250 0.1586 0.01471 0.00900 -0.0535 0.8895 0.7452
0.000 0.2028 0.01439 0.00865 -0.0565 0.8868 0.7497
0.250 0.2462 0.01405 0.00833 -0.0592 0.8846 0.7537
0.500 0.2684 0.01399 0.00829 -0.0579 0.8745 0.7584
0.750 0.3164 0.01342 0.00770 -0.0612 0.8697 0.7633
1.000 0.3473 0.01304 0.00733 -0.0611 0.8579 0.7674
1.250 0.3834 0.01254 0.00683 -0.0618 0.8454 0.7715
1.500 0.4166 0.01206 0.00632 -0.0618 0.8279 0.7764
1.750 0.4467 0.01175 0.00596 -0.0616 0.8102 0.7813
2.000 0.4742 0.01156 0.00580 -0.0610 0.7955 0.7857
2.250 0.5017 0.01143 0.00569 -0.0605 0.7811 0.7909
2.500 0.5289 0.01134 0.00557 -0.0600 0.7648 0.7966
2.750 0.5543 0.01121 0.00548 -0.0591 0.7459 0.8015
3.000 0.5805 0.01112 0.00537 -0.0582 0.7231 0.8073
3.250 0.6045 0.01108 0.00529 -0.0571 0.6937 0.8136
3.500 0.6267 0.01106 0.00521 -0.0555 0.6545 0.8196
3.750 0.6468 0.01119 0.00514 -0.0535 0.5904 0.8268
4.000 0.6590 0.01171 0.00515 -0.0501 0.4827 0.8337
4.250 0.6646 0.01272 0.00548 -0.0460 0.3533 0.8428
4.500 0.6707 0.01390 0.00601 -0.0424 0.2308 0.8524
4.750 0.6833 0.01482 0.00654 -0.0398 0.1714 0.8637
5.000 0.7008 0.01540 0.00702 -0.0380 0.1500 0.8771
5.250 0.7203 0.01590 0.00751 -0.0365 0.1388 0.8953
5.500 0.7451 0.01648 0.00808 -0.0362 0.1307 0.9271
5.750 0.7819 0.01710 0.00875 -0.0386 0.1238 1.0000
6.000 0.8070 0.01772 0.00929 -0.0386 0.1186 1.0000
6.250 0.8312 0.01870 0.01014 -0.0385 0.1143 1.0000
6.500 0.8569 0.01927 0.01076 -0.0383 0.1114 1.0000
6.750 0.8823 0.01993 0.01142 -0.0381 0.1081 1.0000
7.000 0.9073 0.02063 0.01208 -0.0379 0.1049 1.0000
7.250 0.9346 0.02179 0.01314 -0.0382 0.1015 1.0000
7.500 0.9613 0.02273 0.01414 -0.0382 0.0995 1.0000
7.750 0.9870 0.02352 0.01503 -0.0380 0.0975 1.0000
8.000 1.0128 0.02442 0.01602 -0.0378 0.0953 1.0000
8.250 1.0378 0.02532 0.01697 -0.0375 0.0930 1.0000
8.500 1.0628 0.02628 0.01793 -0.0373 0.0908 1.0000
8.750 1.0908 0.02793 0.01956 -0.0378 0.0885 1.0000
9.000 1.1158 0.02973 0.02154 -0.0377 0.0871 1.0000
9.250 1.1368 0.03084 0.02287 -0.0367 0.0859 1.0000
9.500 1.1568 0.03208 0.02433 -0.0356 0.0843 1.0000
9.750 1.1762 0.03340 0.02584 -0.0345 0.0825 1.0000
10.000 1.1953 0.03487 0.02749 -0.0335 0.0810 1.0000
10.250 1.2148 0.03620 0.02892 -0.0326 0.0793 1.0000
10.500 1.2332 0.03756 0.03033 -0.0317 0.0776 1.0000
10.750 1.2488 0.04145 0.03434 -0.0313 0.0755 1.0000
11.000 1.2545 0.04231 0.03556 -0.0281 0.0743 1.0000
11.250 1.2586 0.04390 0.03749 -0.0252 0.0727 1.0000
11.500 1.2616 0.04584 0.03971 -0.0223 0.0710 1.0000
11.750 1.2647 0.04772 0.04181 -0.0197 0.0695 1.0000
12.000 1.2740 0.04890 0.04306 -0.0178 0.0678 1.0000
12.250 1.2886 0.04994 0.04408 -0.0167 0.0662 1.0000
12.500 1.2955 0.05271 0.04688 -0.0154 0.0647 1.0000
12.750 1.2744 0.05650 0.05094 -0.0110 0.0640 1.0000
13.000 1.2518 0.05875 0.05348 -0.0065 0.0636 1.0000
13.250 1.2258 0.06188 0.05689 -0.0030 0.0631 1.0000
13.500 1.1967 0.06599 0.06127 -0.0009 0.0628 1.0000
13.750 1.1644 0.07124 0.06676 -0.0003 0.0628 1.0000
14.000 1.1276 0.07776 0.07350 -0.0014 0.0630 1.0000
14.250 1.0877 0.08590 0.08184 -0.0046 0.0633 1.0000
14.500 1.0455 0.09622 0.09232 -0.0099 0.0638 1.0000
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Polar data table (+)
Polar graphs
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