EPPLER 858 AIRFOIL (e858-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 858 AIRFOIL (e858-il) Reynolds number: 200,000 Max Cl/Cd: 51.48 at α=8.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e858-il-200000-n5.txt Download as CSV file: xf-e858-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 858 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.250 -0.5268 0.13681 0.13210 -0.0509 1.0000 0.0192
-18.000 -0.5522 0.12796 0.12307 -0.0551 1.0000 0.0193
-17.750 -0.5674 0.12144 0.11643 -0.0580 1.0000 0.0195
-17.500 -0.5823 0.11518 0.11003 -0.0609 1.0000 0.0199
-17.250 -0.5912 0.11021 0.10495 -0.0629 1.0000 0.0200
-17.000 -0.5987 0.10561 0.10025 -0.0647 1.0000 0.0202
-16.750 -0.6056 0.10121 0.09574 -0.0664 1.0000 0.0205
-16.500 -0.6101 0.09739 0.09188 -0.0677 1.0000 0.0207
-16.250 -0.6135 0.09386 0.08834 -0.0688 1.0000 0.0210
-16.000 -0.6170 0.09036 0.08479 -0.0699 1.0000 0.0212
-15.750 -0.6206 0.08692 0.08132 -0.0709 1.0000 0.0215
-15.500 -0.6243 0.08357 0.07793 -0.0718 1.0000 0.0217
-15.250 -0.6284 0.08025 0.07457 -0.0725 1.0000 0.0221
-15.000 -0.6316 0.07718 0.07145 -0.0731 1.0000 0.0224
-14.750 -0.6356 0.07412 0.06834 -0.0736 1.0000 0.0228
-14.500 -0.6392 0.07128 0.06544 -0.0738 1.0000 0.0232
-14.250 -0.6431 0.06850 0.06260 -0.0739 1.0000 0.0237
-14.000 -0.6473 0.06588 0.05995 -0.0739 1.0000 0.0239
-13.750 -0.6356 0.06226 0.05630 -0.0782 0.9971 0.0245
-13.500 -0.6217 0.05900 0.05299 -0.0824 0.9937 0.0252
-13.250 -0.6087 0.05590 0.04982 -0.0861 0.9899 0.0261
-13.000 -0.5953 0.05299 0.04683 -0.0895 0.9852 0.0270
-12.750 -0.5809 0.04994 0.04373 -0.0937 0.9811 0.0280
-12.500 -0.5732 0.04717 0.04092 -0.0957 0.9729 0.0290
-12.250 -0.5674 0.04462 0.03833 -0.0969 0.9619 0.0301
-12.000 -0.5660 0.04225 0.03593 -0.0971 0.9452 0.0313
-11.750 -0.5646 0.03983 0.03348 -0.0975 0.9266 0.0325
-11.500 -0.5524 0.03751 0.03109 -0.0994 0.9115 0.0347
-11.250 -0.5362 0.03491 0.02843 -0.1026 0.8961 0.0364
-11.000 -0.5107 0.03245 0.02586 -0.1069 0.8804 0.0395
-10.750 -0.4757 0.02992 0.02321 -0.1132 0.8627 0.0437
-10.500 -0.4292 0.02744 0.02059 -0.1216 0.8415 0.0490
-10.250 -0.3759 0.02519 0.01820 -0.1313 0.8170 0.0565
-10.000 -0.3372 0.02348 0.01631 -0.1375 0.7895 0.0639
-9.750 -0.3229 0.02226 0.01492 -0.1383 0.7647 0.0696
-9.500 -0.3167 0.02147 0.01399 -0.1364 0.7432 0.0749
-9.250 -0.3075 0.02081 0.01323 -0.1345 0.7250 0.0812
-9.000 -0.2969 0.02024 0.01255 -0.1326 0.7084 0.0884
-8.750 -0.2854 0.01970 0.01193 -0.1306 0.6928 0.0967
-8.500 -0.2731 0.01919 0.01136 -0.1286 0.6788 0.1061
-8.250 -0.2591 0.01871 0.01082 -0.1268 0.6657 0.1166
-8.000 -0.2446 0.01823 0.01031 -0.1249 0.6526 0.1287
-7.750 -0.2287 0.01777 0.00982 -0.1233 0.6410 0.1428
-7.500 -0.2123 0.01732 0.00935 -0.1217 0.6295 0.1592
-7.250 -0.1950 0.01687 0.00889 -0.1203 0.6193 0.1781
-7.000 -0.1777 0.01641 0.00847 -0.1188 0.6085 0.2008
-6.750 -0.1592 0.01601 0.00812 -0.1174 0.5989 0.2277
-6.500 -0.1393 0.01571 0.00787 -0.1162 0.5887 0.2569
-6.250 -0.1180 0.01555 0.00770 -0.1151 0.5797 0.2825
-6.000 -0.0949 0.01545 0.00759 -0.1142 0.5709 0.3033
-5.750 -0.0716 0.01542 0.00749 -0.1133 0.5623 0.3202
-5.500 -0.0475 0.01541 0.00741 -0.1125 0.5543 0.3340
-5.250 -0.0232 0.01542 0.00730 -0.1117 0.5457 0.3469
-4.750 0.0254 0.01549 0.00718 -0.1101 0.5299 0.3667
-4.500 0.0496 0.01554 0.00721 -0.1092 0.5222 0.3739
-4.250 0.0741 0.01561 0.00714 -0.1085 0.5157 0.3819
-4.000 0.0993 0.01562 0.00708 -0.1079 0.5091 0.3888
-3.750 0.1239 0.01568 0.00710 -0.1071 0.5024 0.3949
-3.500 0.1483 0.01577 0.00706 -0.1064 0.4963 0.4017
-3.250 0.1734 0.01580 0.00698 -0.1057 0.4901 0.4082
-3.000 0.1978 0.01585 0.00704 -0.1049 0.4837 0.4136
-2.750 0.2218 0.01595 0.00705 -0.1041 0.4777 0.4201
-2.500 0.2466 0.01603 0.00701 -0.1035 0.4725 0.4261
-2.250 0.2715 0.01604 0.00696 -0.1029 0.4670 0.4303
-2.000 0.2958 0.01606 0.00696 -0.1021 0.4618 0.4338
-1.750 0.3198 0.01612 0.00696 -0.1013 0.4571 0.4374
-1.500 0.3443 0.01618 0.00695 -0.1006 0.4528 0.4413
-1.250 0.3689 0.01621 0.00693 -0.0999 0.4481 0.4450
-1.000 0.3928 0.01626 0.00690 -0.0992 0.4433 0.4489
-0.750 0.4161 0.01632 0.00688 -0.0983 0.4388 0.4524
-0.500 0.4397 0.01640 0.00691 -0.0975 0.4349 0.4558
-0.250 0.4637 0.01645 0.00697 -0.0967 0.4307 0.4591
0.000 0.4877 0.01651 0.00702 -0.0960 0.4267 0.4627
0.250 0.5114 0.01660 0.00706 -0.0952 0.4229 0.4665
0.500 0.5350 0.01671 0.00710 -0.0944 0.4195 0.4706
0.750 0.5588 0.01685 0.00714 -0.0937 0.4163 0.4745
1.000 0.5827 0.01694 0.00725 -0.0930 0.4132 0.4780
1.250 0.6060 0.01703 0.00737 -0.0922 0.4097 0.4816
1.500 0.6289 0.01714 0.00748 -0.0913 0.4061 0.4854
1.750 0.6518 0.01728 0.00759 -0.0904 0.4027 0.4896
2.000 0.6749 0.01745 0.00769 -0.0896 0.3997 0.4941
2.250 0.6987 0.01763 0.00782 -0.0890 0.3970 0.4983
2.500 0.7222 0.01779 0.00800 -0.0883 0.3945 0.5025
2.750 0.7451 0.01794 0.00820 -0.0875 0.3918 0.5068
3.000 0.7678 0.01811 0.00839 -0.0866 0.3891 0.5113
3.250 0.7901 0.01830 0.00858 -0.0857 0.3863 0.5161
3.500 0.8122 0.01850 0.00876 -0.0848 0.3836 0.5210
3.750 0.8340 0.01868 0.00895 -0.0839 0.3811 0.5259
4.000 0.8567 0.01890 0.00915 -0.0831 0.3786 0.5315
4.250 0.8797 0.01914 0.00938 -0.0824 0.3763 0.5373
4.500 0.9010 0.01936 0.00965 -0.0815 0.3741 0.5430
4.750 0.9218 0.01957 0.00994 -0.0804 0.3718 0.5483
5.000 0.9425 0.01980 0.01023 -0.0794 0.3696 0.5547
5.250 0.9631 0.02005 0.01051 -0.0783 0.3673 0.5622
5.500 0.9834 0.02029 0.01078 -0.0772 0.3651 0.5693
5.750 1.0041 0.02054 0.01106 -0.0762 0.3630 0.5773
6.000 1.0258 0.02081 0.01132 -0.0754 0.3609 0.5859
6.250 1.0488 0.02110 0.01161 -0.0749 0.3589 0.5945
6.500 1.0661 0.02140 0.01203 -0.0734 0.3570 0.6043
6.750 1.0841 0.02172 0.01245 -0.0721 0.3550 0.6155
7.000 1.1021 0.02204 0.01287 -0.0708 0.3530 0.6285
7.250 1.1197 0.02236 0.01329 -0.0694 0.3511 0.6427
7.500 1.1367 0.02269 0.01371 -0.0680 0.3491 0.6591
7.750 1.1533 0.02301 0.01412 -0.0665 0.3471 0.6779
8.000 1.1717 0.02332 0.01451 -0.0654 0.3452 0.7012
8.250 1.1920 0.02362 0.01490 -0.0645 0.3434 0.7326
8.500 1.2150 0.02386 0.01526 -0.0641 0.3416 0.7868
8.750 1.2422 0.02413 0.01587 -0.0650 0.3398 1.0000
9.000 1.2558 0.02471 0.01652 -0.0635 0.3380 1.0000
9.250 1.2698 0.02531 0.01717 -0.0620 0.3362 1.0000
9.500 1.2831 0.02594 0.01784 -0.0606 0.3342 1.0000
9.750 1.2970 0.02657 0.01850 -0.0592 0.3323 1.0000
10.000 1.3108 0.02720 0.01916 -0.0579 0.3303 1.0000
10.250 1.3255 0.02782 0.01978 -0.0568 0.3285 1.0000
10.500 1.3426 0.02840 0.02036 -0.0559 0.3269 1.0000
10.750 1.3627 0.02892 0.02086 -0.0555 0.3254 1.0000
11.000 1.3809 0.02956 0.02150 -0.0548 0.3239 1.0000
11.250 1.3842 0.03070 0.02277 -0.0527 0.3221 1.0000
11.500 1.3879 0.03190 0.02408 -0.0508 0.3202 1.0000
11.750 1.3918 0.03315 0.02543 -0.0490 0.3180 1.0000
12.000 1.3976 0.03437 0.02672 -0.0476 0.3159 1.0000
12.250 1.4052 0.03553 0.02794 -0.0463 0.3140 1.0000
12.500 1.4147 0.03663 0.02909 -0.0453 0.3122 1.0000
12.750 1.4265 0.03763 0.03012 -0.0445 0.3107 1.0000
13.000 1.4436 0.03835 0.03084 -0.0441 0.3092 1.0000
13.250 1.4668 0.03877 0.03121 -0.0441 0.3077 1.0000
13.500 1.4441 0.04203 0.03471 -0.0416 0.3052 1.0000
13.750 1.4244 0.04544 0.03831 -0.0397 0.3023 1.0000
14.000 1.4122 0.04856 0.04157 -0.0385 0.2996 1.0000
14.250 1.4084 0.05111 0.04420 -0.0378 0.2973 1.0000
14.500 1.4130 0.05297 0.04611 -0.0374 0.2953 1.0000
14.750 1.4280 0.05389 0.04703 -0.0372 0.2935 1.0000
15.000 1.4513 0.05410 0.04722 -0.0372 0.2922 1.0000
15.500 1.2258 0.08469 0.07850 -0.0382 0.2742 1.0000
15.750 1.2711 0.08184 0.07562 -0.0377 0.2749 1.0000
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