EPPLER E852 AIRFOIL (e852-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: EPPLER E852 AIRFOIL (e852-il) Reynolds number: 100,000 Max Cl/Cd: 58.64 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e852-il-100000.txt Download as CSV file: xf-e852-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER E852 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4178 0.10293 0.09807 -0.0405 1.0000 0.0908
-9.000 -0.4352 0.10015 0.09543 -0.0436 1.0000 0.0942
-8.750 -0.4591 0.09755 0.09298 -0.0467 1.0000 0.0949
-8.500 -0.4326 0.09323 0.08863 -0.0416 1.0000 0.0990
-8.250 -0.4349 0.09056 0.08603 -0.0406 1.0000 0.1027
-8.000 -0.4519 0.08810 0.08370 -0.0407 1.0000 0.1060
-7.750 -0.4812 0.08624 0.08200 -0.0399 1.0000 0.1072
-7.500 -0.5114 0.08306 0.07895 -0.0425 1.0000 0.1077
-7.250 -0.5428 0.08005 0.07587 -0.0451 1.0000 0.1083
-7.000 -0.5155 0.07796 0.07397 -0.0356 1.0000 0.1129
-6.750 -0.5259 0.07502 0.07108 -0.0355 1.0000 0.1161
-6.500 -0.5609 0.07016 0.06588 -0.0441 1.0000 0.1222
-5.750 -0.5438 0.06075 0.05665 -0.0387 1.0000 0.1411
-5.500 -0.5387 0.05724 0.05304 -0.0396 1.0000 0.1534
-5.250 -0.5298 0.05406 0.04978 -0.0399 1.0000 0.1676
-5.000 -0.4723 0.03735 0.03076 -0.0498 1.0000 0.0501
-4.750 -0.4432 0.03482 0.02723 -0.0492 1.0000 0.0429
-4.500 -0.4183 0.03094 0.02296 -0.0495 1.0000 0.0418
-4.250 -0.3930 0.02847 0.02007 -0.0492 1.0000 0.0417
-4.000 -0.3687 0.02619 0.01758 -0.0492 1.0000 0.0470
-3.750 -0.3444 0.02485 0.01604 -0.0485 1.0000 0.0533
-3.500 -0.3191 0.02291 0.01407 -0.0479 1.0000 0.0603
-3.250 -0.2946 0.02179 0.01294 -0.0475 1.0000 0.0824
-3.000 -0.2670 0.01996 0.01151 -0.0481 1.0000 0.1395
-2.750 -0.2424 0.01809 0.01165 -0.0479 1.0000 0.5657
-2.500 -0.2167 0.01869 0.01214 -0.0470 0.9963 0.6288
-2.250 -0.1895 0.01925 0.01263 -0.0464 0.9920 0.6736
-2.000 -0.1643 0.01960 0.01294 -0.0457 0.9872 0.7053
-1.750 -0.1374 0.02005 0.01331 -0.0452 0.9829 0.7399
-1.500 -0.1163 0.02029 0.01356 -0.0435 0.9782 0.7703
-1.250 -0.0917 0.02044 0.01363 -0.0431 0.9733 0.7946
-1.000 -0.0612 0.02069 0.01380 -0.0439 0.9693 0.8134
-0.750 -0.0378 0.02071 0.01369 -0.0437 0.9640 0.8328
-0.500 -0.0103 0.02083 0.01377 -0.0440 0.9592 0.8536
-0.250 0.0181 0.02098 0.01390 -0.0446 0.9546 0.8791
0.000 0.0426 0.02095 0.01389 -0.0445 0.9490 0.9148
0.250 0.0952 0.02105 0.01394 -0.0507 0.9445 1.0000
0.500 0.1325 0.02138 0.01412 -0.0545 0.9391 1.0000
0.750 0.1718 0.02180 0.01440 -0.0583 0.9337 1.0000
1.000 0.2123 0.02230 0.01479 -0.0620 0.9290 1.0000
1.250 0.2408 0.02268 0.01510 -0.0633 0.9221 1.0000
1.500 0.2828 0.02320 0.01554 -0.0668 0.9174 1.0000
1.750 0.3065 0.02360 0.01591 -0.0670 0.9094 1.0000
2.000 0.3486 0.02406 0.01636 -0.0703 0.9043 1.0000
2.250 0.3718 0.02449 0.01682 -0.0702 0.8955 1.0000
2.500 0.4118 0.02490 0.01727 -0.0729 0.8894 1.0000
2.750 0.4402 0.02528 0.01769 -0.0737 0.8803 1.0000
3.000 0.4705 0.02567 0.01814 -0.0746 0.8713 1.0000
3.250 0.5163 0.02584 0.01842 -0.0779 0.8646 1.0000
3.500 0.5455 0.02609 0.01884 -0.0783 0.8534 1.0000
3.750 0.5794 0.02623 0.01911 -0.0794 0.8422 1.0000
4.000 0.6194 0.02608 0.01915 -0.0811 0.8306 1.0000
4.250 0.6699 0.02528 0.01859 -0.0836 0.8171 1.0000
4.500 0.7569 0.02228 0.01609 -0.0899 0.8006 1.0000
4.750 0.8176 0.01994 0.01410 -0.0920 0.7800 1.0000
5.000 0.8670 0.01771 0.01216 -0.0920 0.7480 1.0000
5.250 0.8964 0.01635 0.01098 -0.0892 0.7003 1.0000
5.500 0.9118 0.01555 0.01000 -0.0840 0.5791 1.0000
5.750 0.8993 0.01797 0.01033 -0.0758 0.2693 1.0000
6.000 0.8929 0.02093 0.01206 -0.0704 0.1415 1.0000
6.250 0.9006 0.02306 0.01383 -0.0670 0.0961 1.0000
6.500 0.9121 0.02545 0.01603 -0.0645 0.0659 1.0000
6.750 0.9337 0.02766 0.01826 -0.0630 0.0457 1.0000
7.000 0.9682 0.03105 0.02170 -0.0635 0.0375 1.0000
7.250 1.0016 0.03424 0.02518 -0.0636 0.0340 1.0000
7.500 1.0252 0.03754 0.02861 -0.0633 0.0302 1.0000
7.750 1.0427 0.04103 0.03260 -0.0615 0.0282 1.0000
8.000 1.0575 0.04394 0.03603 -0.0591 0.0271 1.0000
8.250 1.0686 0.04789 0.04044 -0.0566 0.0275 1.0000
8.500 1.0749 0.05222 0.04517 -0.0540 0.0281 1.0000
8.750 1.0816 0.05841 0.05161 -0.0524 0.0295 1.0000
9.000 1.0767 0.06065 0.05473 -0.0465 0.0336 1.0000
9.250 1.0662 0.06565 0.06012 -0.0428 0.0365 1.0000
9.500 1.0581 0.07016 0.06482 -0.0402 0.0386 1.0000
9.750 0.9597 0.08600 0.08198 -0.0325 0.1167 1.0000
10.000 0.9288 0.09033 0.08643 -0.0310 0.1167 1.0000
10.250 0.9065 0.09585 0.09203 -0.0313 0.1168 1.0000
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Polar data table (+)
Polar graphs
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