EPPLER 856 AIRFOIL (e856-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 856 AIRFOIL (e856-il) Reynolds number: 500,000 Max Cl/Cd: 99.72 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e856-il-500000-n5.txt Download as CSV file: xf-e856-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 856 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.750 -0.5644 0.14045 0.13750 -0.0420 1.0000 0.0061
-17.500 -0.5883 0.13114 0.12807 -0.0461 1.0000 0.0061
-17.250 -0.6080 0.12314 0.11997 -0.0497 1.0000 0.0060
-17.000 -0.6264 0.11566 0.11240 -0.0531 1.0000 0.0061
-16.750 -0.6450 0.10838 0.10502 -0.0564 1.0000 0.0061
-16.500 -0.6614 0.10165 0.09817 -0.0594 1.0000 0.0060
-16.250 -0.6762 0.09539 0.09180 -0.0622 1.0000 0.0059
-16.000 -0.6951 0.08865 0.08497 -0.0653 1.0000 0.0060
-15.750 -0.7104 0.08273 0.07895 -0.0680 1.0000 0.0061
-15.500 -0.7248 0.07718 0.07330 -0.0704 1.0000 0.0061
-15.250 -0.7363 0.07229 0.06831 -0.0724 1.0000 0.0060
-15.000 -0.7468 0.06776 0.06369 -0.0742 1.0000 0.0060
-14.750 -0.7625 0.06277 0.05862 -0.0761 1.0000 0.0062
-14.500 -0.7716 0.05900 0.05476 -0.0772 1.0000 0.0061
-14.250 -0.7815 0.05515 0.05083 -0.0785 0.9998 0.0061
-14.000 -0.7786 0.05089 0.04646 -0.0829 0.9981 0.0062
-13.750 -0.7734 0.04708 0.04255 -0.0869 0.9960 0.0063
-13.500 -0.7629 0.04376 0.03912 -0.0911 0.9939 0.0064
-13.250 -0.7556 0.04056 0.03583 -0.0943 0.9911 0.0064
-13.000 -0.7444 0.03773 0.03291 -0.0976 0.9879 0.0065
-12.750 -0.7291 0.03502 0.03010 -0.1014 0.9849 0.0067
-12.500 -0.7164 0.03258 0.02758 -0.1040 0.9809 0.0069
-12.250 -0.7048 0.03035 0.02527 -0.1060 0.9750 0.0070
-12.000 -0.6989 0.02825 0.02309 -0.1067 0.9662 0.0071
-11.750 -0.6976 0.02640 0.02115 -0.1062 0.9519 0.0071
-11.500 -0.6939 0.02458 0.01923 -0.1062 0.9362 0.0073
-11.250 -0.6779 0.02302 0.01756 -0.1073 0.9231 0.0074
-11.000 -0.6485 0.02173 0.01615 -0.1097 0.9126 0.0077
-10.750 -0.6082 0.02035 0.01466 -0.1142 0.9029 0.0080
-10.500 -0.5577 0.01904 0.01324 -0.1207 0.8912 0.0086
-10.250 -0.4949 0.01796 0.01202 -0.1293 0.8759 0.0095
-10.000 -0.4478 0.01714 0.01102 -0.1346 0.8525 0.0105
-9.750 -0.4198 0.01657 0.01027 -0.1357 0.8247 0.0114
-9.500 -0.3996 0.01616 0.00970 -0.1350 0.8010 0.0122
-9.250 -0.3814 0.01575 0.00917 -0.1338 0.7810 0.0132
-9.000 -0.3631 0.01536 0.00867 -0.1325 0.7635 0.0145
-8.750 -0.3439 0.01502 0.00821 -0.1313 0.7473 0.0158
-8.500 -0.3245 0.01468 0.00778 -0.1301 0.7319 0.0178
-8.250 -0.3043 0.01436 0.00737 -0.1291 0.7176 0.0201
-7.750 -0.2617 0.01377 0.00665 -0.1272 0.6914 0.0272
-7.500 -0.2394 0.01350 0.00631 -0.1264 0.6804 0.0314
-7.000 -0.1940 0.01296 0.00569 -0.1249 0.6591 0.0423
-6.750 -0.1709 0.01270 0.00539 -0.1243 0.6489 0.0493
-6.500 -0.1474 0.01246 0.00512 -0.1236 0.6385 0.0576
-6.250 -0.1237 0.01220 0.00485 -0.1231 0.6291 0.0684
-6.000 -0.0998 0.01194 0.00459 -0.1225 0.6202 0.0818
-5.750 -0.0754 0.01168 0.00435 -0.1221 0.6123 0.0977
-5.500 -0.0509 0.01144 0.00411 -0.1217 0.6040 0.1163
-5.250 -0.0265 0.01115 0.00387 -0.1212 0.5963 0.1403
-5.000 -0.0019 0.01087 0.00364 -0.1209 0.5882 0.1680
-4.750 0.0224 0.01055 0.00341 -0.1205 0.5809 0.2055
-4.500 0.0470 0.01020 0.00319 -0.1202 0.5734 0.2542
-4.250 0.0717 0.00997 0.00305 -0.1198 0.5669 0.2999
-4.000 0.0981 0.00982 0.00298 -0.1196 0.5607 0.3348
-3.750 0.1245 0.00976 0.00292 -0.1194 0.5542 0.3596
-3.500 0.1510 0.00975 0.00289 -0.1191 0.5482 0.3764
-3.250 0.1781 0.00974 0.00285 -0.1189 0.5418 0.3891
-3.000 0.2046 0.00976 0.00283 -0.1187 0.5357 0.3993
-2.750 0.2317 0.00979 0.00280 -0.1185 0.5306 0.4080
-2.500 0.2588 0.00979 0.00279 -0.1183 0.5253 0.4170
-2.250 0.2856 0.00984 0.00278 -0.1181 0.5202 0.4263
-2.000 0.3122 0.00989 0.00280 -0.1179 0.5154 0.4376
-1.750 0.3395 0.00991 0.00281 -0.1177 0.5106 0.4455
-1.500 0.3663 0.00994 0.00281 -0.1175 0.5055 0.4509
-1.250 0.3927 0.01001 0.00281 -0.1172 0.5009 0.4553
-1.000 0.4199 0.01005 0.00281 -0.1171 0.4971 0.4594
-0.750 0.4470 0.01006 0.00282 -0.1170 0.4931 0.4632
-0.500 0.4736 0.01011 0.00284 -0.1167 0.4890 0.4672
-0.250 0.4999 0.01018 0.00287 -0.1164 0.4848 0.4716
0.000 0.5266 0.01024 0.00289 -0.1162 0.4812 0.4757
0.250 0.5535 0.01027 0.00293 -0.1161 0.4774 0.4792
0.500 0.5800 0.01032 0.00297 -0.1159 0.4738 0.4834
0.750 0.6062 0.01039 0.00303 -0.1156 0.4704 0.4880
1.000 0.6321 0.01048 0.00308 -0.1152 0.4671 0.4922
1.250 0.6588 0.01053 0.00314 -0.1150 0.4640 0.4959
1.500 0.6852 0.01058 0.00321 -0.1148 0.4606 0.5004
1.750 0.7113 0.01065 0.00328 -0.1145 0.4572 0.5053
2.000 0.7369 0.01074 0.00335 -0.1141 0.4540 0.5101
2.250 0.7620 0.01083 0.00344 -0.1136 0.4512 0.5143
2.500 0.7876 0.01090 0.00353 -0.1133 0.4486 0.5190
2.750 0.8134 0.01096 0.00362 -0.1129 0.4457 0.5247
3.000 0.8386 0.01104 0.00371 -0.1125 0.4426 0.5301
3.250 0.8632 0.01111 0.00382 -0.1119 0.4394 0.5356
3.500 0.8877 0.01122 0.00393 -0.1113 0.4367 0.5415
4.000 0.9371 0.01142 0.00418 -0.1103 0.4318 0.5541
4.250 0.9621 0.01150 0.00431 -0.1098 0.4291 0.5615
4.500 0.9865 0.01159 0.00446 -0.1093 0.4262 0.5686
4.750 1.0105 0.01171 0.00461 -0.1086 0.4232 0.5764
5.000 1.0342 0.01184 0.00477 -0.1080 0.4206 0.5843
5.250 1.0576 0.01199 0.00495 -0.1073 0.4181 0.5939
5.500 1.0819 0.01210 0.00513 -0.1067 0.4158 0.6040
5.750 1.1063 0.01221 0.00531 -0.1062 0.4131 0.6151
6.000 1.1299 0.01232 0.00550 -0.1055 0.4102 0.6262
6.250 1.1532 0.01246 0.00570 -0.1048 0.4074 0.6386
6.500 1.1758 0.01261 0.00591 -0.1040 0.4048 0.6533
7.000 1.2201 0.01290 0.00637 -0.1022 0.3993 0.6892
7.250 1.2426 0.01300 0.00660 -0.1014 0.3961 0.7106
7.500 1.2638 0.01313 0.00684 -0.1003 0.3923 0.7360
7.750 1.2828 0.01326 0.00708 -0.0988 0.3880 0.7703
8.250 1.3253 0.01329 0.00757 -0.0966 0.3786 1.0000
8.500 1.3441 0.01355 0.00783 -0.0953 0.3728 1.0000
8.750 1.3631 0.01382 0.00811 -0.0940 0.3672 1.0000
9.000 1.3828 0.01408 0.00840 -0.0928 0.3612 1.0000
9.250 1.3993 0.01442 0.00874 -0.0911 0.3551 1.0000
9.500 1.4187 0.01471 0.00907 -0.0899 0.3499 1.0000
9.750 1.4363 0.01505 0.00944 -0.0885 0.3436 1.0000
10.000 1.4513 0.01548 0.00988 -0.0867 0.3373 1.0000
10.250 1.4685 0.01586 0.01030 -0.0853 0.3302 1.0000
10.500 1.4810 0.01640 0.01084 -0.0832 0.3223 1.0000
10.750 1.4955 0.01690 0.01137 -0.0815 0.3134 1.0000
11.000 1.5065 0.01756 0.01203 -0.0794 0.3039 1.0000
11.250 1.5144 0.01838 0.01284 -0.0769 0.2925 1.0000
11.500 1.5209 0.01931 0.01376 -0.0744 0.2787 1.0000
11.750 1.5229 0.02053 0.01493 -0.0716 0.2629 1.0000
12.000 1.5222 0.02200 0.01635 -0.0686 0.2455 1.0000
12.250 1.5190 0.02372 0.01803 -0.0657 0.2283 1.0000
12.500 1.5135 0.02575 0.02001 -0.0629 0.2117 1.0000
12.750 1.5077 0.02795 0.02218 -0.0604 0.1971 1.0000
13.000 1.5011 0.03039 0.02460 -0.0582 0.1833 1.0000
13.250 1.4943 0.03300 0.02719 -0.0563 0.1713 1.0000
13.500 1.4862 0.03586 0.03005 -0.0546 0.1597 1.0000
13.750 1.4780 0.03890 0.03309 -0.0532 0.1484 1.0000
14.000 1.4715 0.04191 0.03611 -0.0522 0.1388 1.0000
14.250 1.4639 0.04515 0.03936 -0.0512 0.1305 1.0000
14.500 1.4549 0.04865 0.04288 -0.0505 0.1214 1.0000
14.750 1.4492 0.05192 0.04618 -0.0500 0.1141 1.0000
15.250 1.4359 0.05894 0.05327 -0.0495 0.1005 1.0000
15.500 1.4279 0.06275 0.05709 -0.0494 0.0945 1.0000
15.750 1.4240 0.06615 0.06054 -0.0495 0.0887 1.0000
16.250 1.4137 0.07347 0.06792 -0.0500 0.0778 1.0000
16.500 1.4078 0.07731 0.07179 -0.0504 0.0728 1.0000
16.750 1.4048 0.08085 0.07537 -0.0509 0.0680 1.0000
17.000 1.4013 0.08452 0.07907 -0.0514 0.0639 1.0000
17.250 1.3988 0.08810 0.08269 -0.0521 0.0599 1.0000
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Polar data table (+)
Polar graphs
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