E211 (10.96%) (e211-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: E211 (10.96%) (e211-il) Reynolds number: 50,000 Max Cl/Cd: 39.19 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e211-il-50000-n5.txt Download as CSV file: xf-e211-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E211 (10.96%)
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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4473 0.10493 0.09761 -0.0406 1.0000 0.0489
-9.750 -0.4466 0.10129 0.09402 -0.0409 1.0000 0.0484
-9.500 -0.4481 0.09746 0.09025 -0.0416 1.0000 0.0479
-9.250 -0.4516 0.09343 0.08630 -0.0424 1.0000 0.0474
-9.000 -0.4576 0.08911 0.08207 -0.0436 1.0000 0.0469
-8.750 -0.4651 0.08476 0.07781 -0.0448 1.0000 0.0463
-8.500 -0.4775 0.07982 0.07296 -0.0466 1.0000 0.0457
-8.250 -0.4960 0.07509 0.06833 -0.0482 1.0000 0.0452
-8.000 -0.5123 0.07018 0.06344 -0.0502 1.0000 0.0446
-7.750 -0.5259 0.06548 0.05868 -0.0514 1.0000 0.0441
-7.500 -0.5347 0.06097 0.05402 -0.0521 1.0000 0.0437
-7.250 -0.5387 0.05656 0.04937 -0.0525 1.0000 0.0434
-7.000 -0.5374 0.05225 0.04475 -0.0529 1.0000 0.0432
-6.750 -0.5310 0.04821 0.04033 -0.0530 1.0000 0.0432
-6.500 -0.5200 0.04451 0.03620 -0.0530 1.0000 0.0435
-6.250 -0.5052 0.04133 0.03258 -0.0529 1.0000 0.0444
-6.000 -0.4877 0.03852 0.02925 -0.0526 1.0000 0.0462
-5.750 -0.4678 0.03600 0.02619 -0.0522 1.0000 0.0483
-5.500 -0.4472 0.03375 0.02359 -0.0516 1.0000 0.0501
-5.250 -0.4267 0.03193 0.02162 -0.0509 1.0000 0.0519
-5.000 -0.4056 0.03038 0.01991 -0.0499 1.0000 0.0543
-4.750 -0.3842 0.02903 0.01836 -0.0488 1.0000 0.0574
-4.500 -0.3627 0.02783 0.01688 -0.0475 1.0000 0.0620
-4.250 -0.3419 0.02676 0.01583 -0.0468 1.0000 0.0711
-4.000 -0.3203 0.02569 0.01473 -0.0462 1.0000 0.0839
-3.750 -0.2980 0.02451 0.01366 -0.0460 1.0000 0.1125
-3.500 -0.2742 0.02320 0.01283 -0.0467 1.0000 0.1852
-3.250 -0.2492 0.02183 0.01211 -0.0476 1.0000 0.3028
-3.000 -0.2302 0.02117 0.01227 -0.0463 1.0000 0.4542
-2.750 -0.2068 0.02135 0.01261 -0.0452 0.9965 0.5648
-2.500 -0.1739 0.02172 0.01291 -0.0458 0.9874 0.6357
-2.250 -0.1436 0.02201 0.01309 -0.0457 0.9778 0.6844
-2.000 -0.1139 0.02222 0.01319 -0.0456 0.9682 0.7254
-1.750 -0.0846 0.02236 0.01323 -0.0453 0.9586 0.7597
-1.500 -0.0572 0.02237 0.01312 -0.0447 0.9480 0.7910
-1.250 -0.0310 0.02230 0.01296 -0.0440 0.9369 0.8204
-1.000 -0.0041 0.02219 0.01277 -0.0436 0.9259 0.8492
-0.750 0.0262 0.02206 0.01255 -0.0438 0.9158 0.8785
-0.500 0.0645 0.02193 0.01232 -0.0457 0.9069 0.9085
-0.250 0.1069 0.02182 0.01212 -0.0489 0.8965 0.9404
0.000 0.1582 0.02169 0.01186 -0.0541 0.8870 0.9819
0.250 0.2003 0.02162 0.01164 -0.0578 0.8779 1.0000
0.500 0.2337 0.02164 0.01154 -0.0597 0.8659 1.0000
0.750 0.2687 0.02169 0.01147 -0.0618 0.8547 1.0000
1.000 0.3078 0.02168 0.01136 -0.0644 0.8456 1.0000
1.250 0.3455 0.02168 0.01129 -0.0666 0.8357 1.0000
1.500 0.3792 0.02177 0.01132 -0.0681 0.8242 1.0000
1.750 0.4153 0.02183 0.01134 -0.0698 0.8137 1.0000
2.000 0.4559 0.02179 0.01129 -0.0722 0.8050 1.0000
2.500 0.5199 0.02205 0.01156 -0.0740 0.7806 1.0000
2.750 0.5537 0.02215 0.01170 -0.0751 0.7690 1.0000
3.000 0.5899 0.02218 0.01176 -0.0764 0.7583 1.0000
3.250 0.6240 0.02226 0.01190 -0.0774 0.7464 1.0000
3.500 0.6545 0.02245 0.01217 -0.0778 0.7329 1.0000
3.750 0.6851 0.02263 0.01242 -0.0781 0.7192 1.0000
4.000 0.7157 0.02280 0.01267 -0.0784 0.7050 1.0000
4.250 0.7461 0.02296 0.01292 -0.0785 0.6900 1.0000
4.500 0.7764 0.02311 0.01320 -0.0786 0.6743 1.0000
4.750 0.8067 0.02324 0.01342 -0.0785 0.6577 1.0000
5.000 0.8333 0.02346 0.01375 -0.0779 0.6394 1.0000
5.250 0.8583 0.02372 0.01416 -0.0771 0.6196 1.0000
5.500 0.8856 0.02387 0.01441 -0.0764 0.5992 1.0000
5.750 0.9084 0.02414 0.01480 -0.0751 0.5764 1.0000
6.000 0.9334 0.02430 0.01505 -0.0739 0.5527 1.0000
6.250 0.9532 0.02462 0.01552 -0.0721 0.5259 1.0000
6.500 0.9726 0.02494 0.01594 -0.0702 0.4971 1.0000
6.750 0.9910 0.02529 0.01635 -0.0682 0.4654 1.0000
7.000 1.0068 0.02577 0.01688 -0.0658 0.4297 1.0000
7.250 1.0212 0.02634 0.01742 -0.0633 0.3906 1.0000
7.500 1.0330 0.02711 0.01811 -0.0606 0.3472 1.0000
7.750 1.0424 0.02813 0.01903 -0.0578 0.3015 1.0000
8.000 1.0498 0.02943 0.02012 -0.0549 0.2583 1.0000
8.250 1.0551 0.03091 0.02141 -0.0520 0.2209 1.0000
8.500 1.0594 0.03259 0.02292 -0.0492 0.1898 1.0000
8.750 1.0637 0.03440 0.02463 -0.0466 0.1622 1.0000
9.000 1.0680 0.03635 0.02651 -0.0441 0.1374 1.0000
9.250 1.0701 0.03844 0.02851 -0.0418 0.1147 1.0000
9.500 1.0705 0.04063 0.03059 -0.0397 0.0949 1.0000
9.750 1.0720 0.04294 0.03292 -0.0378 0.0782 1.0000
10.000 1.0740 0.04540 0.03538 -0.0362 0.0667 1.0000
10.250 1.0775 0.04788 0.03793 -0.0347 0.0580 1.0000
10.500 1.0862 0.05036 0.04060 -0.0332 0.0521 1.0000
10.750 1.0935 0.05283 0.04317 -0.0320 0.0477 1.0000
11.000 1.1036 0.05541 0.04590 -0.0308 0.0441 1.0000
11.250 1.1123 0.05812 0.04892 -0.0298 0.0406 1.0000
11.500 1.1176 0.06094 0.05192 -0.0291 0.0384 1.0000
11.750 1.1223 0.06392 0.05501 -0.0284 0.0367 1.0000
12.000 1.1279 0.06740 0.05866 -0.0278 0.0357 1.0000
12.250 1.1259 0.07149 0.06319 -0.0275 0.0351 1.0000
12.500 1.1192 0.07605 0.06809 -0.0277 0.0347 1.0000
12.750 1.1083 0.08110 0.07347 -0.0287 0.0345 1.0000
13.000 1.0942 0.08675 0.07940 -0.0304 0.0344 1.0000
13.250 1.0778 0.09297 0.08588 -0.0329 0.0344 1.0000
13.500 1.0594 0.09990 0.09304 -0.0363 0.0345 1.0000
13.750 1.0400 0.10754 0.10087 -0.0407 0.0347 1.0000
14.000 1.0200 0.11599 0.10945 -0.0458 0.0349 1.0000
|
Polar data table (+)
Polar graphs
<< Back to E211 (10.96%) (e211-il)