EPPLER 857 AIRFOIL (e857-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 857 AIRFOIL (e857-il) Reynolds number: 200,000 Max Cl/Cd: 62.29 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e857-il-200000-n5.txt Download as CSV file: xf-e857-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 857 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
------ -------- --------- --------- -------- -------- --------
-16.250 -0.5383 0.11204 0.10755 -0.0611 1.0000 0.0159
-16.000 -0.5645 0.10336 0.09870 -0.0653 1.0000 0.0158
-15.750 -0.5832 0.09655 0.09174 -0.0684 1.0000 0.0158
-15.500 -0.5983 0.09063 0.08569 -0.0711 1.0000 0.0160
-15.250 -0.6104 0.08554 0.08048 -0.0731 1.0000 0.0161
-15.000 -0.6208 0.08089 0.07572 -0.0749 1.0000 0.0162
-14.750 -0.6306 0.07660 0.07133 -0.0763 1.0000 0.0164
-14.500 -0.6389 0.07273 0.06734 -0.0774 1.0000 0.0166
-14.250 -0.6461 0.06922 0.06374 -0.0782 1.0000 0.0168
-14.000 -0.6530 0.06597 0.06041 -0.0787 1.0000 0.0169
-13.750 -0.6607 0.06286 0.05721 -0.0789 1.0000 0.0172
-13.500 -0.6678 0.06014 0.05447 -0.0788 1.0000 0.0174
-13.250 -0.6711 0.05747 0.05176 -0.0792 0.9995 0.0174
-13.000 -0.6577 0.05422 0.04844 -0.0835 0.9962 0.0178
-12.750 -0.6441 0.05111 0.04526 -0.0876 0.9926 0.0183
-12.500 -0.6311 0.04813 0.04219 -0.0912 0.9878 0.0189
-12.250 -0.6147 0.04539 0.03933 -0.0950 0.9836 0.0195
-12.000 -0.6030 0.04280 0.03664 -0.0974 0.9765 0.0200
-11.750 -0.5930 0.04019 0.03398 -0.0997 0.9677 0.0206
-11.500 -0.5875 0.03778 0.03153 -0.1008 0.9550 0.0212
-11.250 -0.5813 0.03559 0.02928 -0.1016 0.9400 0.0218
-11.000 -0.5723 0.03346 0.02706 -0.1027 0.9256 0.0228
-10.750 -0.5604 0.03134 0.02484 -0.1043 0.9118 0.0237
-10.500 -0.5449 0.02929 0.02271 -0.1065 0.8980 0.0252
-10.250 -0.5259 0.02733 0.02061 -0.1091 0.8842 0.0269
-10.000 -0.4969 0.02552 0.01870 -0.1127 0.8712 0.0290
-9.750 -0.4612 0.02399 0.01704 -0.1166 0.8564 0.0321
-9.500 -0.4197 0.02267 0.01558 -0.1213 0.8409 0.0360
-9.250 -0.3745 0.02150 0.01430 -0.1267 0.8239 0.0416
-9.000 -0.3377 0.02056 0.01323 -0.1300 0.8049 0.0472
-8.750 -0.3088 0.01983 0.01238 -0.1315 0.7861 0.0534
-8.500 -0.2848 0.01922 0.01167 -0.1318 0.7682 0.0601
-8.250 -0.2630 0.01870 0.01105 -0.1315 0.7516 0.0676
-8.000 -0.2420 0.01824 0.01050 -0.1309 0.7362 0.0762
-7.750 -0.2211 0.01781 0.00998 -0.1302 0.7219 0.0856
-7.500 -0.2015 0.01740 0.00950 -0.1291 0.7077 0.0956
-7.250 -0.1814 0.01699 0.00903 -0.1282 0.6948 0.1070
-7.000 -0.1611 0.01658 0.00856 -0.1272 0.6827 0.1201
-6.750 -0.1412 0.01613 0.00811 -0.1262 0.6709 0.1365
-6.500 -0.1204 0.01571 0.00769 -0.1254 0.6605 0.1586
-6.250 -0.0998 0.01526 0.00728 -0.1245 0.6498 0.1867
-6.000 -0.0792 0.01480 0.00691 -0.1236 0.6399 0.2241
-5.750 -0.0578 0.01445 0.00666 -0.1227 0.6298 0.2681
-5.500 -0.0345 0.01427 0.00653 -0.1220 0.6203 0.3041
-5.250 -0.0101 0.01422 0.00643 -0.1214 0.6109 0.3303
-5.000 0.0150 0.01421 0.00635 -0.1208 0.6025 0.3503
-4.750 0.0402 0.01424 0.00630 -0.1203 0.5941 0.3665
-4.500 0.0656 0.01429 0.00627 -0.1197 0.5866 0.3795
-4.250 0.0912 0.01432 0.00620 -0.1192 0.5784 0.3898
-4.000 0.1167 0.01439 0.00615 -0.1187 0.5710 0.3993
-3.750 0.1424 0.01440 0.00608 -0.1182 0.5634 0.4070
-3.500 0.1677 0.01447 0.00607 -0.1176 0.5559 0.4153
-3.250 0.1936 0.01455 0.00602 -0.1172 0.5497 0.4248
-3.000 0.2192 0.01461 0.00607 -0.1167 0.5431 0.4329
-2.750 0.2451 0.01471 0.00602 -0.1163 0.5370 0.4421
-2.500 0.2707 0.01477 0.00605 -0.1158 0.5315 0.4483
-2.250 0.2965 0.01480 0.00605 -0.1153 0.5254 0.4540
-2.000 0.3223 0.01485 0.00598 -0.1149 0.5196 0.4592
-1.750 0.3480 0.01491 0.00592 -0.1145 0.5144 0.4635
-1.500 0.3737 0.01492 0.00594 -0.1141 0.5088 0.4672
-1.250 0.3994 0.01496 0.00594 -0.1137 0.5037 0.4712
-1.000 0.4251 0.01504 0.00592 -0.1133 0.4992 0.4759
-0.750 0.4514 0.01513 0.00590 -0.1130 0.4950 0.4806
-0.500 0.4771 0.01515 0.00593 -0.1126 0.4904 0.4841
-0.250 0.5024 0.01520 0.00598 -0.1122 0.4858 0.4879
0.000 0.5276 0.01529 0.00601 -0.1117 0.4814 0.4924
0.250 0.5535 0.01541 0.00603 -0.1114 0.4776 0.4973
0.500 0.5790 0.01548 0.00608 -0.1110 0.4734 0.5017
0.750 0.6042 0.01554 0.00617 -0.1105 0.4695 0.5054
1.000 0.6293 0.01563 0.00626 -0.1101 0.4659 0.5098
1.250 0.6547 0.01576 0.00633 -0.1097 0.4625 0.5150
1.500 0.6807 0.01591 0.00640 -0.1094 0.4594 0.5202
1.750 0.7051 0.01598 0.00653 -0.1088 0.4557 0.5245
2.000 0.7293 0.01608 0.00666 -0.1082 0.4520 0.5291
2.250 0.7536 0.01620 0.00678 -0.1076 0.4485 0.5344
2.500 0.7784 0.01635 0.00688 -0.1072 0.4455 0.5404
2.750 0.8037 0.01650 0.00702 -0.1068 0.4428 0.5457
3.000 0.8282 0.01664 0.00720 -0.1063 0.4402 0.5515
3.250 0.8514 0.01677 0.00737 -0.1055 0.4371 0.5576
3.500 0.8742 0.01690 0.00755 -0.1047 0.4339 0.5636
3.750 0.8968 0.01703 0.00772 -0.1038 0.4308 0.5702
4.000 0.9203 0.01720 0.00789 -0.1032 0.4280 0.5780
4.250 0.9450 0.01739 0.00807 -0.1027 0.4256 0.5853
4.500 0.9693 0.01758 0.00830 -0.1023 0.4232 0.5934
4.750 0.9909 0.01776 0.00855 -0.1013 0.4206 0.6018
5.000 1.0123 0.01794 0.00883 -0.1003 0.4178 0.6110
5.250 1.0340 0.01813 0.00909 -0.0993 0.4150 0.6218
5.500 1.0558 0.01832 0.00934 -0.0984 0.4123 0.6334
5.750 1.0784 0.01853 0.00959 -0.0976 0.4099 0.6458
6.000 1.1026 0.01876 0.00984 -0.0972 0.4077 0.6600
6.250 1.1250 0.01899 0.01015 -0.0964 0.4056 0.6758
6.500 1.1436 0.01922 0.01053 -0.0949 0.4032 0.6945
7.000 1.1813 0.01964 0.01124 -0.0921 0.3980 0.7460
7.250 1.2000 0.01981 0.01157 -0.0906 0.3954 0.7870
7.500 1.2230 0.01987 0.01187 -0.0899 0.3931 0.8888
7.750 1.2510 0.02012 0.01212 -0.0904 0.3910 1.0000
8.000 1.2758 0.02048 0.01245 -0.0903 0.3890 1.0000
8.250 1.2918 0.02087 0.01293 -0.0886 0.3867 1.0000
8.500 1.3080 0.02128 0.01341 -0.0871 0.3841 1.0000
8.750 1.3250 0.02168 0.01387 -0.0857 0.3814 1.0000
9.000 1.3425 0.02208 0.01431 -0.0844 0.3789 1.0000
9.250 1.3614 0.02249 0.01474 -0.0833 0.3768 1.0000
9.500 1.3821 0.02288 0.01514 -0.0826 0.3747 1.0000
9.750 1.4058 0.02325 0.01549 -0.0823 0.3727 1.0000
10.000 1.4179 0.02381 0.01615 -0.0803 0.3702 1.0000
10.250 1.4287 0.02442 0.01688 -0.0782 0.3675 1.0000
10.500 1.4411 0.02502 0.01756 -0.0764 0.3649 1.0000
10.750 1.4545 0.02560 0.01821 -0.0748 0.3623 1.0000
11.000 1.4688 0.02614 0.01881 -0.0733 0.3598 1.0000
11.250 1.4870 0.02662 0.01930 -0.0725 0.3574 1.0000
11.500 1.5056 0.02712 0.01980 -0.0717 0.3549 1.0000
11.750 1.5054 0.02818 0.02104 -0.0686 0.3516 1.0000
12.000 1.5089 0.02919 0.02217 -0.0662 0.3480 1.0000
12.250 1.5157 0.03009 0.02315 -0.0643 0.3445 1.0000
12.500 1.5284 0.03077 0.02383 -0.0630 0.3412 1.0000
12.750 1.5404 0.03156 0.02465 -0.0617 0.3380 1.0000
13.000 1.5338 0.03333 0.02660 -0.0590 0.3339 1.0000
13.250 1.5331 0.03489 0.02828 -0.0570 0.3298 1.0000
13.500 1.5394 0.03609 0.02953 -0.0556 0.3260 1.0000
13.750 1.5534 0.03684 0.03027 -0.0548 0.3226 1.0000
14.000 1.5394 0.03965 0.03328 -0.0526 0.3180 1.0000
14.250 1.5339 0.04200 0.03576 -0.0511 0.3135 1.0000
14.500 1.5394 0.04352 0.03732 -0.0502 0.3094 1.0000
14.750 1.5402 0.04555 0.03942 -0.0493 0.3053 1.0000
15.000 1.5207 0.04958 0.04363 -0.0481 0.2995 1.0000
15.250 1.5197 0.05197 0.04608 -0.0474 0.2947 1.0000
15.500 1.5195 0.05436 0.04852 -0.0469 0.2899 1.0000
15.750 1.4920 0.05986 0.05421 -0.0465 0.2833 1.0000
16.000 1.4955 0.06201 0.05637 -0.0463 0.2781 1.0000
16.250 1.4708 0.06761 0.06211 -0.0464 0.2712 1.0000
16.500 1.4599 0.07169 0.06626 -0.0466 0.2644 1.0000
16.750 1.4488 0.07589 0.07053 -0.0470 0.2578 1.0000
17.000 1.4307 0.08113 0.07585 -0.0476 0.2498 1.0000
17.250 1.4206 0.08542 0.08021 -0.0483 0.2426 1.0000
17.500 1.4098 0.08986 0.08470 -0.0490 0.2343 1.0000
17.750 1.3962 0.09479 0.08969 -0.0500 0.2264 1.0000
18.000 1.3990 0.09739 0.09228 -0.0505 0.2185 1.0000
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Polar data table (+)
Polar graphs
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