E71 (5.15%) (e71-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: E71 (5.15%) (e71-il) Reynolds number: 100,000 Max Cl/Cd: 74.01 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e71-il-100000-n5.txt Download as CSV file: xf-e71-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E71 (5.15%)
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
------ -------- --------- --------- -------- -------- --------
-7.000 -0.3750 0.09795 0.09332 -0.0198 1.0000 0.0395
-6.750 -0.3801 0.09616 0.09160 -0.0182 1.0000 0.0407
-6.500 -0.3836 0.09415 0.08966 -0.0173 1.0000 0.0419
-6.250 -0.3843 0.09187 0.08744 -0.0176 1.0000 0.0433
-6.000 -0.3827 0.08958 0.08522 -0.0193 1.0000 0.0449
-5.750 -0.3734 0.08723 0.08292 -0.0261 1.0000 0.0463
-5.500 -0.3562 0.08390 0.07958 -0.0337 1.0000 0.0468
-5.250 -0.3363 0.07991 0.07555 -0.0402 1.0000 0.0470
-5.000 -0.3286 0.07456 0.07027 -0.0394 0.9982 0.0479
-4.750 -0.3119 0.07063 0.06634 -0.0398 0.9952 0.0494
-4.500 -0.2841 0.06647 0.06213 -0.0448 0.9919 0.0513
-4.250 -0.2473 0.06169 0.05726 -0.0530 0.9882 0.0534
-4.000 -0.1906 0.05528 0.05065 -0.0681 0.9855 0.0629
-3.750 -0.1291 0.04956 0.04457 -0.0823 0.9837 0.0748
-3.500 -0.0632 0.03957 0.03393 -0.0933 0.9841 0.0336
-3.250 -0.0175 0.03476 0.02882 -0.1004 0.9836 0.0315
-3.000 0.0336 0.03039 0.02389 -0.1074 0.9836 0.0297
-2.750 0.0828 0.02684 0.01958 -0.1130 0.9837 0.0282
-2.500 0.1280 0.02419 0.01626 -0.1170 0.9834 0.0272
-2.250 0.1693 0.02235 0.01390 -0.1198 0.9825 0.0268
-2.000 0.2060 0.02103 0.01226 -0.1217 0.9803 0.0271
-1.750 0.2415 0.02004 0.01106 -0.1233 0.9774 0.0278
-1.500 0.2776 0.01931 0.01018 -0.1251 0.9744 0.0296
-1.250 0.3144 0.01882 0.00955 -0.1272 0.9715 0.0369
-1.000 0.3508 0.01843 0.00905 -0.1290 0.9682 0.0451
-0.750 0.3854 0.01795 0.00857 -0.1305 0.9635 0.0639
-0.500 0.4243 0.01700 0.00858 -0.1336 0.9610 0.3504
-0.250 0.4601 0.01644 0.00864 -0.1353 0.9579 0.5965
0.000 0.4761 0.01567 0.00845 -0.1322 0.9485 1.0000
0.250 0.5127 0.01577 0.00836 -0.1340 0.9434 1.0000
0.500 0.5444 0.01583 0.00830 -0.1348 0.9354 1.0000
0.750 0.5792 0.01587 0.00824 -0.1362 0.9288 1.0000
1.000 0.6136 0.01588 0.00818 -0.1375 0.9213 1.0000
1.250 0.6463 0.01588 0.00814 -0.1384 0.9129 1.0000
1.500 0.6845 0.01576 0.00802 -0.1402 0.9063 1.0000
2.000 0.7503 0.01553 0.00787 -0.1416 0.8859 1.0000
2.250 0.7867 0.01528 0.00769 -0.1428 0.8763 1.0000
2.500 0.8234 0.01502 0.00750 -0.1440 0.8648 1.0000
2.750 0.8566 0.01483 0.00749 -0.1445 0.8493 1.0000
3.000 0.8909 0.01464 0.00740 -0.1452 0.8316 1.0000
3.250 0.9290 0.01437 0.00724 -0.1465 0.8118 1.0000
3.500 0.9642 0.01420 0.00717 -0.1472 0.7843 1.0000
3.750 0.9996 0.01408 0.00711 -0.1478 0.7467 1.0000
4.000 1.0348 0.01409 0.00720 -0.1484 0.6933 1.0000
4.250 1.0658 0.01440 0.00730 -0.1481 0.6173 1.0000
4.500 1.0892 0.01513 0.00765 -0.1466 0.5235 1.0000
4.750 1.1019 0.01669 0.00828 -0.1435 0.3737 1.0000
5.000 1.1145 0.01847 0.00916 -0.1412 0.2352 1.0000
5.250 1.1329 0.01980 0.01008 -0.1398 0.1569 1.0000
5.500 1.1487 0.02165 0.01125 -0.1381 0.0639 1.0000
5.750 1.1665 0.02337 0.01277 -0.1363 0.0278 1.0000
6.000 1.1854 0.02500 0.01466 -0.1344 0.0212 1.0000
6.250 1.2050 0.02632 0.01618 -0.1329 0.0174 1.0000
6.500 1.2225 0.02798 0.01797 -0.1312 0.0145 1.0000
6.750 1.2406 0.02962 0.01987 -0.1294 0.0134 1.0000
7.000 1.2583 0.03157 0.02206 -0.1275 0.0128 1.0000
7.250 1.2771 0.03381 0.02453 -0.1258 0.0123 1.0000
7.500 1.2973 0.03637 0.02737 -0.1243 0.0120 1.0000
7.750 1.3175 0.03929 0.03063 -0.1229 0.0117 1.0000
8.000 1.3357 0.04260 0.03437 -0.1212 0.0116 1.0000
8.250 1.3502 0.04630 0.03858 -0.1190 0.0115 1.0000
8.500 1.3599 0.05032 0.04313 -0.1164 0.0115 1.0000
8.750 1.3642 0.05458 0.04793 -0.1133 0.0115 1.0000
9.000 1.3631 0.05902 0.05287 -0.1100 0.0116 1.0000
9.250 1.3564 0.06357 0.05798 -0.1064 0.0117 1.0000
9.500 1.3438 0.06782 0.06261 -0.1026 0.0118 1.0000
9.750 1.3266 0.07190 0.06700 -0.0988 0.0119 1.0000
10.000 1.3075 0.07636 0.07174 -0.0960 0.0119 1.0000
10.250 1.2870 0.08135 0.07698 -0.0945 0.0120 1.0000
10.500 1.2664 0.08688 0.08263 -0.0946 0.0121 1.0000
10.750 1.2450 0.09328 0.08924 -0.0965 0.0122 1.0000
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Polar data table (+)
Polar graphs
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