E209 (13.72%) (e209-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: E209 (13.72%) (e209-il) Reynolds number: 500,000 Max Cl/Cd: 100.05 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e209-il-500000.txt Download as CSV file: xf-e209-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: E209 (13.72%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.000 -0.5615 0.11409 0.11167 -0.0285 1.0000 0.0137
-13.750 -0.6075 0.09791 0.09543 -0.0361 1.0000 0.0132
-13.500 -0.6551 0.08286 0.08026 -0.0450 1.0000 0.0125
-13.250 -0.6968 0.07060 0.06781 -0.0533 1.0000 0.0121
-13.000 -0.7148 0.06399 0.06106 -0.0580 1.0000 0.0123
-12.750 -0.7451 0.05610 0.05297 -0.0631 1.0000 0.0120
-12.500 -0.7642 0.05060 0.04729 -0.0663 1.0000 0.0120
-12.250 -0.7858 0.04534 0.04181 -0.0686 1.0000 0.0118
-12.000 -0.8028 0.04127 0.03754 -0.0695 1.0000 0.0117
-11.750 -0.8108 0.03883 0.03496 -0.0690 1.0000 0.0120
-11.500 -0.8291 0.03577 0.03167 -0.0668 1.0000 0.0119
-11.250 -0.8372 0.03441 0.03020 -0.0635 1.0000 0.0121
-11.000 -0.8491 0.03281 0.02845 -0.0589 1.0000 0.0122
-10.750 -0.8528 0.03099 0.02644 -0.0553 1.0000 0.0123
-10.500 -0.8508 0.02974 0.02503 -0.0522 1.0000 0.0127
-10.250 -0.8470 0.02834 0.02345 -0.0492 1.0000 0.0129
-10.000 -0.8392 0.02751 0.02245 -0.0465 1.0000 0.0133
-9.750 -0.8311 0.02629 0.02106 -0.0438 1.0000 0.0134
-9.500 -0.8261 0.02424 0.01882 -0.0408 1.0000 0.0138
-9.250 -0.8186 0.02263 0.01715 -0.0381 1.0000 0.0143
-9.000 -0.7993 0.02155 0.01601 -0.0374 0.9990 0.0147
-8.750 -0.7648 0.02045 0.01483 -0.0396 0.9960 0.0154
-8.500 -0.7296 0.01945 0.01374 -0.0418 0.9931 0.0163
-8.250 -0.6960 0.01849 0.01266 -0.0435 0.9890 0.0171
-8.000 -0.6631 0.01704 0.01110 -0.0454 0.9852 0.0183
-7.750 -0.6281 0.01622 0.01028 -0.0476 0.9817 0.0199
-7.500 -0.5950 0.01557 0.00958 -0.0490 0.9759 0.0216
-7.250 -0.5598 0.01454 0.00846 -0.0511 0.9720 0.0234
-7.000 -0.5290 0.01376 0.00766 -0.0521 0.9647 0.0256
-6.750 -0.4931 0.01325 0.00709 -0.0539 0.9589 0.0284
-6.500 -0.4650 0.01246 0.00629 -0.0543 0.9479 0.0322
-6.250 -0.4329 0.01198 0.00576 -0.0552 0.9362 0.0365
-6.000 -0.4018 0.01127 0.00508 -0.0561 0.9215 0.0490
-5.750 -0.3713 0.01059 0.00451 -0.0568 0.9025 0.0786
-5.500 -0.3430 0.01012 0.00409 -0.0570 0.8793 0.1097
-5.250 -0.3177 0.00973 0.00374 -0.0566 0.8538 0.1435
-4.500 -0.2464 0.00869 0.00291 -0.0546 0.7860 0.2796
-4.250 -0.2229 0.00835 0.00272 -0.0539 0.7671 0.3415
-4.000 -0.1983 0.00817 0.00263 -0.0533 0.7501 0.3972
-3.750 -0.1723 0.00812 0.00257 -0.0529 0.7343 0.4334
-3.500 -0.1459 0.00810 0.00250 -0.0525 0.7201 0.4543
-3.250 -0.1190 0.00810 0.00243 -0.0522 0.7070 0.4692
-3.000 -0.0920 0.00811 0.00237 -0.0520 0.6950 0.4835
-2.750 -0.0650 0.00813 0.00232 -0.0517 0.6840 0.4974
-2.500 -0.0376 0.00814 0.00227 -0.0516 0.6732 0.5109
-2.250 -0.0104 0.00813 0.00224 -0.0514 0.6635 0.5219
-1.750 0.0445 0.00815 0.00216 -0.0511 0.6455 0.5423
-1.500 0.0718 0.00816 0.00213 -0.0509 0.6375 0.5525
-1.250 0.0993 0.00815 0.00211 -0.0508 0.6292 0.5626
-1.000 0.1269 0.00818 0.00209 -0.0507 0.6219 0.5731
-0.750 0.1544 0.00816 0.00208 -0.0506 0.6143 0.5834
-0.500 0.1818 0.00818 0.00208 -0.0505 0.6075 0.5939
-0.250 0.2095 0.00817 0.00208 -0.0504 0.6003 0.6055
0.000 0.2369 0.00821 0.00209 -0.0503 0.5940 0.6176
0.250 0.2644 0.00817 0.00211 -0.0502 0.5872 0.6300
0.500 0.2916 0.00818 0.00213 -0.0501 0.5808 0.6433
0.750 0.3190 0.00818 0.00216 -0.0499 0.5747 0.6578
1.000 0.3463 0.00817 0.00220 -0.0498 0.5684 0.6735
1.250 0.3733 0.00820 0.00224 -0.0496 0.5626 0.6914
1.500 0.4004 0.00816 0.00229 -0.0494 0.5563 0.7117
1.750 0.4270 0.00816 0.00235 -0.0491 0.5505 0.7342
2.000 0.4534 0.00815 0.00243 -0.0487 0.5447 0.7600
2.250 0.4795 0.00811 0.00251 -0.0483 0.5386 0.7899
2.500 0.5047 0.00812 0.00260 -0.0476 0.5331 0.8237
2.750 0.5298 0.00806 0.00270 -0.0468 0.5270 0.8617
3.000 0.5553 0.00806 0.00280 -0.0460 0.5209 0.9023
3.250 0.5870 0.00813 0.00293 -0.0466 0.5141 0.9394
3.500 0.6250 0.00821 0.00301 -0.0487 0.5061 0.9634
3.750 0.6639 0.00831 0.00311 -0.0511 0.4983 0.9790
4.000 0.7046 0.00841 0.00320 -0.0540 0.4900 0.9885
4.250 0.7458 0.00849 0.00330 -0.0569 0.4812 0.9968
4.500 0.7773 0.00862 0.00339 -0.0579 0.4733 1.0000
4.750 0.8000 0.00868 0.00349 -0.0569 0.4649 1.0000
5.000 0.8224 0.00881 0.00359 -0.0559 0.4568 1.0000
5.250 0.8456 0.00891 0.00371 -0.0550 0.4476 1.0000
5.500 0.8686 0.00903 0.00384 -0.0540 0.4385 1.0000
5.750 0.8912 0.00919 0.00397 -0.0530 0.4286 1.0000
6.000 0.9148 0.00931 0.00412 -0.0522 0.4174 1.0000
6.250 0.9382 0.00946 0.00429 -0.0514 0.4056 1.0000
6.500 0.9614 0.00964 0.00446 -0.0506 0.3929 1.0000
6.750 0.9845 0.00984 0.00465 -0.0497 0.3784 1.0000
7.000 1.0070 0.01008 0.00486 -0.0488 0.3598 1.0000
7.250 1.0284 0.01039 0.00511 -0.0477 0.3364 1.0000
7.500 1.0485 0.01081 0.00541 -0.0464 0.3055 1.0000
7.750 1.0665 0.01137 0.00581 -0.0449 0.2686 1.0000
8.000 1.0830 0.01204 0.00629 -0.0432 0.2295 1.0000
8.250 1.0984 0.01278 0.00685 -0.0413 0.1946 1.0000
8.500 1.1139 0.01350 0.00743 -0.0395 0.1641 1.0000
8.750 1.1288 0.01424 0.00802 -0.0376 0.1374 1.0000
9.000 1.1429 0.01497 0.00864 -0.0356 0.1140 1.0000
9.250 1.1570 0.01567 0.00925 -0.0336 0.0952 1.0000
9.500 1.1695 0.01637 0.00988 -0.0313 0.0794 1.0000
9.750 1.1795 0.01705 0.01051 -0.0286 0.0674 1.0000
10.000 1.1887 0.01777 0.01121 -0.0258 0.0572 1.0000
10.250 1.1971 0.01857 0.01198 -0.0231 0.0483 1.0000
10.500 1.2039 0.01948 0.01287 -0.0203 0.0407 1.0000
10.750 1.2122 0.02036 0.01376 -0.0179 0.0354 1.0000
11.000 1.2184 0.02140 0.01483 -0.0154 0.0309 1.0000
11.250 1.2243 0.02253 0.01597 -0.0132 0.0275 1.0000
11.500 1.2276 0.02390 0.01740 -0.0110 0.0247 1.0000
11.750 1.2347 0.02514 0.01869 -0.0094 0.0223 1.0000
12.000 1.2320 0.02718 0.02079 -0.0073 0.0201 1.0000
12.250 1.2383 0.02870 0.02239 -0.0062 0.0190 1.0000
12.500 1.2433 0.03040 0.02417 -0.0052 0.0175 1.0000
12.750 1.2448 0.03251 0.02633 -0.0043 0.0162 1.0000
13.000 1.2365 0.03564 0.02954 -0.0034 0.0154 1.0000
13.250 1.2424 0.03756 0.03156 -0.0029 0.0145 1.0000
13.500 1.2448 0.03987 0.03396 -0.0026 0.0137 1.0000
13.750 1.2448 0.04249 0.03666 -0.0024 0.0132 1.0000
14.000 1.2444 0.04521 0.03946 -0.0023 0.0127 1.0000
14.250 1.2408 0.04833 0.04266 -0.0024 0.0124 1.0000
14.500 1.2324 0.05208 0.04649 -0.0026 0.0120 1.0000
14.750 1.2270 0.05561 0.05012 -0.0030 0.0115 1.0000
15.000 1.2260 0.05875 0.05338 -0.0034 0.0112 1.0000
15.250 1.2248 0.06200 0.05673 -0.0039 0.0110 1.0000
15.500 1.2253 0.06513 0.05996 -0.0046 0.0107 1.0000
15.750 1.2237 0.06860 0.06353 -0.0055 0.0104 1.0000
16.000 1.2214 0.07227 0.06728 -0.0065 0.0101 1.0000
16.250 1.2198 0.07591 0.07101 -0.0076 0.0099 1.0000
16.500 1.2177 0.07971 0.07488 -0.0088 0.0096 1.0000
16.750 1.2150 0.08363 0.07889 -0.0102 0.0095 1.0000
17.000 1.2105 0.08790 0.08323 -0.0117 0.0092 1.0000
17.250 1.2056 0.09224 0.08766 -0.0132 0.0090 1.0000
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Polar data table (+)
Polar graphs
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