EPPLER 855 AIRFOIL (e855-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 855 AIRFOIL (e855-il) Reynolds number: 500,000 Max Cl/Cd: 111.99 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e855-il-500000.txt Download as CSV file: xf-e855-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 855 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.5062 0.08438 0.08198 -0.0589 1.0000 0.0112
-12.250 -0.5346 0.07531 0.07282 -0.0639 1.0000 0.0110
-12.000 -0.5615 0.06777 0.06519 -0.0680 1.0000 0.0108
-11.750 -0.5879 0.06131 0.05861 -0.0713 1.0000 0.0108
-11.500 -0.6117 0.05613 0.05333 -0.0732 1.0000 0.0106
-11.250 -0.6415 0.05112 0.04819 -0.0741 1.0000 0.0104
-11.000 -0.6578 0.04568 0.04254 -0.0787 0.9979 0.0103
-10.750 -0.6585 0.03971 0.03622 -0.0874 0.9917 0.0103
-10.500 -0.6530 0.03464 0.03073 -0.0938 0.9844 0.0101
-10.250 -0.6395 0.03102 0.02676 -0.0962 0.9769 0.0101
-10.000 -0.6154 0.02785 0.02323 -0.0992 0.9731 0.0099
-9.750 -0.5968 0.02569 0.02085 -0.0996 0.9656 0.0100
-9.500 -0.5684 0.02375 0.01872 -0.1015 0.9618 0.0101
-9.250 -0.5465 0.02221 0.01703 -0.1016 0.9543 0.0103
-9.000 -0.5173 0.02074 0.01541 -0.1030 0.9496 0.0107
-8.750 -0.4930 0.01950 0.01406 -0.1032 0.9421 0.0109
-8.500 -0.4637 0.01840 0.01284 -0.1042 0.9365 0.0114
-8.250 -0.4397 0.01686 0.01121 -0.1046 0.9281 0.0120
-8.000 -0.4067 0.01583 0.01013 -0.1064 0.9220 0.0129
-7.750 -0.3722 0.01497 0.00919 -0.1084 0.9143 0.0140
-7.500 -0.3319 0.01388 0.00801 -0.1117 0.9074 0.0160
-7.250 -0.2880 0.01308 0.00713 -0.1157 0.8981 0.0200
-7.000 -0.2417 0.01232 0.00636 -0.1202 0.8871 0.0277
-6.750 -0.2017 0.01178 0.00575 -0.1232 0.8712 0.0375
-6.500 -0.1682 0.01136 0.00526 -0.1247 0.8532 0.0478
-6.250 -0.1389 0.01104 0.00487 -0.1253 0.8350 0.0601
-6.000 -0.1126 0.01068 0.00451 -0.1253 0.8173 0.0790
-5.750 -0.0874 0.01037 0.00419 -0.1251 0.8005 0.1027
-5.500 -0.0631 0.01001 0.00387 -0.1247 0.7849 0.1348
-5.250 -0.0393 0.00957 0.00355 -0.1243 0.7702 0.1843
-5.000 -0.0165 0.00899 0.00321 -0.1239 0.7564 0.2660
-4.750 0.0076 0.00863 0.00304 -0.1235 0.7433 0.3427
-4.500 0.0334 0.00855 0.00297 -0.1232 0.7308 0.3841
-4.250 0.0598 0.00855 0.00293 -0.1228 0.7193 0.4092
-4.000 0.0865 0.00859 0.00288 -0.1226 0.7082 0.4260
-3.750 0.1132 0.00862 0.00285 -0.1223 0.6974 0.4396
-3.500 0.1400 0.00868 0.00283 -0.1220 0.6874 0.4526
-3.250 0.1669 0.00875 0.00280 -0.1218 0.6776 0.4639
-3.000 0.1939 0.00879 0.00279 -0.1216 0.6684 0.4731
-2.750 0.2210 0.00885 0.00276 -0.1214 0.6601 0.4808
-2.500 0.2481 0.00889 0.00275 -0.1212 0.6514 0.4886
-2.250 0.2752 0.00895 0.00274 -0.1211 0.6436 0.4970
-2.000 0.3023 0.00903 0.00277 -0.1209 0.6356 0.5073
-1.750 0.3294 0.00908 0.00278 -0.1207 0.6288 0.5153
-1.500 0.3567 0.00913 0.00278 -0.1206 0.6216 0.5223
-1.000 0.4113 0.00919 0.00277 -0.1204 0.6085 0.5324
-0.750 0.4386 0.00925 0.00277 -0.1204 0.6023 0.5377
-0.500 0.4661 0.00929 0.00278 -0.1203 0.5967 0.5427
-0.250 0.4934 0.00931 0.00280 -0.1202 0.5909 0.5476
0.000 0.5209 0.00940 0.00282 -0.1202 0.5855 0.5532
0.250 0.5483 0.00942 0.00285 -0.1202 0.5802 0.5584
0.500 0.5754 0.00945 0.00289 -0.1201 0.5748 0.5636
0.750 0.6031 0.00956 0.00294 -0.1201 0.5700 0.5696
1.000 0.6304 0.00959 0.00300 -0.1201 0.5654 0.5751
1.250 0.6575 0.00963 0.00306 -0.1200 0.5605 0.5811
1.500 0.6850 0.00973 0.00311 -0.1200 0.5560 0.5876
1.750 0.7122 0.00979 0.00321 -0.1199 0.5515 0.5940
2.000 0.7394 0.00984 0.00329 -0.1198 0.5471 0.6013
2.250 0.7664 0.00990 0.00337 -0.1198 0.5429 0.6082
2.500 0.7943 0.01004 0.00348 -0.1199 0.5388 0.6165
2.750 0.8208 0.01006 0.00359 -0.1197 0.5347 0.6246
3.000 0.8477 0.01013 0.00369 -0.1196 0.5304 0.6340
3.250 0.8746 0.01021 0.00382 -0.1195 0.5266 0.6434
3.500 0.9022 0.01035 0.00396 -0.1196 0.5227 0.6542
3.750 0.9283 0.01039 0.00410 -0.1193 0.5187 0.6663
4.000 0.9546 0.01045 0.00424 -0.1191 0.5147 0.6795
4.250 0.9812 0.01054 0.00438 -0.1189 0.5108 0.6940
4.500 1.0080 0.01066 0.00456 -0.1188 0.5069 0.7110
4.750 1.0328 0.01069 0.00472 -0.1183 0.5023 0.7303
5.000 1.0573 0.01072 0.00485 -0.1177 0.4972 0.7531
5.250 1.0823 0.01083 0.00502 -0.1172 0.4921 0.7802
5.500 1.1041 0.01079 0.00518 -0.1159 0.4867 0.8162
5.750 1.1224 0.01072 0.00529 -0.1139 0.4804 0.8737
6.000 1.1486 0.01067 0.00539 -0.1135 0.4736 1.0000
6.250 1.1725 0.01078 0.00552 -0.1129 0.4672 1.0000
6.500 1.1969 0.01097 0.00569 -0.1124 0.4614 1.0000
6.750 1.2202 0.01106 0.00585 -0.1116 0.4549 1.0000
7.000 1.2431 0.01125 0.00602 -0.1108 0.4485 1.0000
7.250 1.2661 0.01137 0.00621 -0.1100 0.4420 1.0000
7.500 1.2873 0.01154 0.00639 -0.1088 0.4343 1.0000
7.750 1.3080 0.01168 0.00659 -0.1076 0.4263 1.0000
8.000 1.3263 0.01190 0.00679 -0.1058 0.4176 1.0000
8.250 1.3452 0.01206 0.00701 -0.1042 0.4067 1.0000
8.500 1.3627 0.01230 0.00727 -0.1024 0.3943 1.0000
8.750 1.3798 0.01258 0.00756 -0.1005 0.3809 1.0000
9.000 1.3950 0.01293 0.00789 -0.0984 0.3645 1.0000
9.250 1.4071 0.01340 0.00830 -0.0957 0.3441 1.0000
9.500 1.4163 0.01403 0.00883 -0.0927 0.3159 1.0000
9.750 1.4198 0.01492 0.00956 -0.0888 0.2807 1.0000
10.000 1.4188 0.01608 0.01051 -0.0845 0.2445 1.0000
10.250 1.4170 0.01735 0.01162 -0.0803 0.2135 1.0000
10.500 1.4151 0.01868 0.01282 -0.0763 0.1857 1.0000
10.750 1.4147 0.02004 0.01407 -0.0729 0.1625 1.0000
11.000 1.4129 0.02156 0.01550 -0.0695 0.1428 1.0000
11.250 1.4131 0.02308 0.01697 -0.0666 0.1266 1.0000
11.500 1.4126 0.02476 0.01860 -0.0640 0.1118 1.0000
11.750 1.4129 0.02651 0.02033 -0.0617 0.1003 1.0000
12.000 1.4118 0.02847 0.02227 -0.0595 0.0891 1.0000
12.250 1.4117 0.03049 0.02427 -0.0577 0.0789 1.0000
12.500 1.4131 0.03250 0.02629 -0.0562 0.0708 1.0000
12.750 1.4121 0.03480 0.02861 -0.0548 0.0630 1.0000
13.000 1.4106 0.03726 0.03106 -0.0536 0.0553 1.0000
13.250 1.4121 0.03954 0.03338 -0.0527 0.0499 1.0000
13.500 1.4101 0.04222 0.03607 -0.0518 0.0448 1.0000
13.750 1.4117 0.04465 0.03855 -0.0511 0.0406 1.0000
14.000 1.4101 0.04747 0.04139 -0.0505 0.0365 1.0000
14.250 1.4103 0.05018 0.04416 -0.0501 0.0333 1.0000
14.500 1.4106 0.05295 0.04699 -0.0498 0.0305 1.0000
14.750 1.4067 0.05628 0.05034 -0.0496 0.0274 1.0000
15.000 1.4091 0.05894 0.05309 -0.0495 0.0251 1.0000
15.250 1.4075 0.06215 0.05633 -0.0496 0.0228 1.0000
15.500 1.4047 0.06558 0.05984 -0.0497 0.0207 1.0000
15.750 1.4050 0.06871 0.06305 -0.0500 0.0188 1.0000
16.000 1.4010 0.07244 0.06681 -0.0504 0.0168 1.0000
16.250 1.3994 0.07594 0.07040 -0.0508 0.0154 1.0000
16.500 1.3983 0.07942 0.07394 -0.0514 0.0135 1.0000
16.750 1.3899 0.08403 0.07861 -0.0523 0.0124 1.0000
17.000 1.3904 0.08744 0.08211 -0.0531 0.0109 1.0000
17.250 1.3870 0.09146 0.08620 -0.0541 0.0101 1.0000
17.500 1.3777 0.09646 0.09129 -0.0554 0.0092 1.0000
17.750 1.3773 0.10019 0.09511 -0.0565 0.0081 1.0000
18.000 1.3742 0.10436 0.09937 -0.0579 0.0076 1.0000
18.250 1.3683 0.10904 0.10413 -0.0595 0.0073 1.0000
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Polar data table (+)
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