EPPLER E852 AIRFOIL (e852-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER E852 AIRFOIL (e852-il) Reynolds number: 50,000 Max Cl/Cd: 35.63 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e852-il-50000-n5.txt Download as CSV file: xf-e852-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4235 0.10249 0.09556 -0.0442 1.0000 0.0384
-9.250 -0.4258 0.09869 0.09185 -0.0450 1.0000 0.0375
-9.000 -0.4300 0.09486 0.08812 -0.0460 1.0000 0.0376
-8.750 -0.4352 0.09100 0.08436 -0.0468 1.0000 0.0368
-8.250 -0.4742 0.07898 0.07254 -0.0538 1.0000 0.0308
-8.000 -0.4861 0.07578 0.06943 -0.0537 1.0000 0.0306
-7.750 -0.4977 0.07246 0.06615 -0.0536 1.0000 0.0304
-7.500 -0.5086 0.06920 0.06288 -0.0532 1.0000 0.0301
-7.250 -0.5184 0.06583 0.05945 -0.0527 1.0000 0.0301
-7.000 -0.5257 0.06236 0.05583 -0.0524 1.0000 0.0302
-6.750 -0.5287 0.05881 0.05207 -0.0520 1.0000 0.0302
-6.500 -0.5276 0.05522 0.04813 -0.0519 1.0000 0.0306
-6.250 -0.5224 0.05149 0.04408 -0.0519 1.0000 0.0311
-6.000 -0.5135 0.04775 0.04004 -0.0518 1.0000 0.0317
-5.750 -0.5008 0.04442 0.03637 -0.0518 1.0000 0.0325
-5.500 -0.4843 0.04125 0.03262 -0.0517 1.0000 0.0331
-5.250 -0.4652 0.03833 0.02928 -0.0514 1.0000 0.0339
-5.000 -0.4440 0.03570 0.02623 -0.0510 1.0000 0.0352
-4.750 -0.4217 0.03344 0.02358 -0.0503 1.0000 0.0370
-4.500 -0.3989 0.03159 0.02128 -0.0493 1.0000 0.0414
-4.250 -0.3700 0.02993 0.01948 -0.0501 0.9969 0.0509
-4.000 -0.3402 0.02820 0.01753 -0.0501 0.9939 0.0587
-3.750 -0.3105 0.02682 0.01603 -0.0510 0.9901 0.0788
-3.500 -0.2791 0.02516 0.01440 -0.0525 0.9865 0.1120
-3.250 -0.2470 0.02245 0.01326 -0.0556 0.9843 0.3488
-3.000 -0.2221 0.02256 0.01378 -0.0545 0.9798 0.5450
-2.750 -0.1995 0.02286 0.01389 -0.0528 0.9743 0.6141
-2.500 -0.1769 0.02322 0.01419 -0.0508 0.9695 0.6705
-2.250 -0.1573 0.02334 0.01422 -0.0485 0.9640 0.7086
-2.000 -0.1314 0.02339 0.01406 -0.0480 0.9591 0.7338
-1.750 -0.1020 0.02342 0.01384 -0.0486 0.9549 0.7535
-1.500 -0.0772 0.02338 0.01364 -0.0484 0.9495 0.7704
-1.250 -0.0479 0.02340 0.01349 -0.0490 0.9451 0.7888
-1.000 -0.0215 0.02341 0.01330 -0.0492 0.9403 0.8082
-0.750 0.0041 0.02340 0.01320 -0.0491 0.9350 0.8293
-0.500 0.0344 0.02344 0.01316 -0.0499 0.9309 0.8541
-0.250 0.0603 0.02342 0.01311 -0.0500 0.9254 0.8858
0.000 0.1000 0.02345 0.01304 -0.0531 0.9209 0.9346
0.250 0.1428 0.02358 0.01303 -0.0573 0.9168 1.0000
0.500 0.1704 0.02386 0.01316 -0.0586 0.9104 1.0000
0.750 0.2057 0.02421 0.01337 -0.0612 0.9058 1.0000
1.000 0.2356 0.02457 0.01363 -0.0626 0.9002 1.0000
1.250 0.2663 0.02494 0.01393 -0.0641 0.8944 1.0000
1.500 0.3013 0.02533 0.01426 -0.0662 0.8899 1.0000
1.750 0.3261 0.02573 0.01464 -0.0665 0.8825 1.0000
2.000 0.3620 0.02611 0.01502 -0.0686 0.8777 1.0000
2.250 0.3852 0.02655 0.01552 -0.0685 0.8697 1.0000
2.500 0.4212 0.02692 0.01594 -0.0705 0.8645 1.0000
2.750 0.4443 0.02738 0.01645 -0.0703 0.8558 1.0000
3.000 0.4795 0.02773 0.01690 -0.0720 0.8498 1.0000
3.250 0.5050 0.02816 0.01744 -0.0721 0.8407 1.0000
3.500 0.5330 0.02855 0.01807 -0.0726 0.8318 1.0000
3.750 0.5708 0.02875 0.01847 -0.0744 0.8246 1.0000
4.000 0.5968 0.02910 0.01900 -0.0743 0.8134 1.0000
4.250 0.6259 0.02934 0.01946 -0.0745 0.8019 1.0000
4.500 0.6578 0.02940 0.01979 -0.0748 0.7896 1.0000
4.750 0.6932 0.02916 0.01998 -0.0753 0.7754 1.0000
5.000 0.7425 0.02802 0.01927 -0.0767 0.7577 1.0000
5.250 0.7769 0.02685 0.01846 -0.0753 0.7286 1.0000
5.500 0.8078 0.02543 0.01738 -0.0727 0.6895 1.0000
5.750 0.8221 0.02484 0.01704 -0.0685 0.6409 1.0000
6.000 0.8462 0.02375 0.01596 -0.0647 0.5293 1.0000
6.250 0.8586 0.02518 0.01558 -0.0602 0.2787 1.0000
6.500 0.8558 0.02755 0.01715 -0.0562 0.1800 1.0000
6.750 0.8605 0.02979 0.01905 -0.0534 0.1231 1.0000
7.000 0.8712 0.03188 0.02101 -0.0511 0.0960 1.0000
7.250 0.8862 0.03382 0.02287 -0.0495 0.0708 1.0000
7.500 0.9143 0.03618 0.02532 -0.0489 0.0558 1.0000
7.750 0.9422 0.03848 0.02764 -0.0491 0.0416 1.0000
8.000 0.9919 0.04233 0.03199 -0.0509 0.0344 1.0000
8.250 1.0148 0.04538 0.03522 -0.0505 0.0304 1.0000
8.500 1.0331 0.04882 0.03918 -0.0492 0.0270 1.0000
8.750 1.0459 0.05219 0.04309 -0.0473 0.0247 1.0000
9.000 1.0531 0.05592 0.04730 -0.0450 0.0238 1.0000
9.250 1.0542 0.05973 0.05154 -0.0424 0.0233 1.0000
9.500 1.0498 0.06340 0.05560 -0.0395 0.0231 1.0000
9.750 1.0400 0.06699 0.05951 -0.0364 0.0230 1.0000
10.000 1.0271 0.07069 0.06349 -0.0337 0.0230 1.0000
10.250 1.0115 0.07462 0.06769 -0.0317 0.0230 1.0000
10.500 0.9942 0.07891 0.07220 -0.0307 0.0231 1.0000
10.750 0.9757 0.08364 0.07714 -0.0307 0.0234 1.0000
11.000 0.9557 0.08905 0.08273 -0.0319 0.0236 1.0000
11.250 0.9360 0.09510 0.08892 -0.0344 0.0239 1.0000
11.500 0.9170 0.10196 0.09587 -0.0381 0.0243 1.0000
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Polar data table (+)
Polar graphs
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