EPPLER 856 AIRFOIL (e856-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 856 AIRFOIL (e856-il) Reynolds number: 1,000,000 Max Cl/Cd: 128.93 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e856-il-1000000.txt Download as CSV file: xf-e856-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.250 -0.5906 0.14355 0.14137 -0.0391 1.0000 0.0060
-18.000 -0.6069 0.13573 0.13347 -0.0426 1.0000 0.0060
-17.750 -0.6337 0.12610 0.12371 -0.0471 1.0000 0.0060
-17.500 -0.6382 0.12121 0.11878 -0.0493 1.0000 0.0059
-17.250 -0.6610 0.11289 0.11034 -0.0532 1.0000 0.0059
-17.000 -0.6787 0.10579 0.10314 -0.0566 1.0000 0.0059
-16.500 -0.7170 0.09206 0.08920 -0.0629 1.0000 0.0058
-16.250 -0.7329 0.08596 0.08301 -0.0658 1.0000 0.0058
-16.000 -0.7437 0.08068 0.07762 -0.0682 1.0000 0.0059
-15.750 -0.7542 0.07567 0.07251 -0.0705 1.0000 0.0059
-15.250 -0.7797 0.06602 0.06268 -0.0743 1.0000 0.0059
-15.000 -0.7920 0.06162 0.05820 -0.0758 1.0000 0.0058
-14.750 -0.8161 0.05612 0.05255 -0.0775 1.0000 0.0060
-14.500 -0.8089 0.05443 0.05085 -0.0777 1.0000 0.0059
-14.250 -0.8205 0.05094 0.04728 -0.0782 1.0000 0.0059
-14.000 -0.8419 0.04654 0.04277 -0.0789 0.9999 0.0060
-13.750 -0.8382 0.04220 0.03830 -0.0839 0.9979 0.0061
-13.500 -0.8337 0.03795 0.03393 -0.0890 0.9954 0.0063
-13.250 -0.8155 0.03522 0.03111 -0.0936 0.9937 0.0062
-13.000 -0.8067 0.03202 0.02782 -0.0972 0.9899 0.0064
-12.750 -0.7881 0.02950 0.02522 -0.1012 0.9869 0.0066
-12.500 -0.7638 0.02730 0.02295 -0.1057 0.9848 0.0068
-12.250 -0.7351 0.02541 0.02098 -0.1104 0.9833 0.0070
-12.000 -0.7277 0.02326 0.01875 -0.1115 0.9755 0.0070
-11.750 -0.7026 0.02163 0.01702 -0.1151 0.9726 0.0071
-11.500 -0.6937 0.02044 0.01576 -0.1135 0.9630 0.0073
-11.250 -0.6800 0.01939 0.01465 -0.1124 0.9532 0.0075
-11.000 -0.6605 0.01857 0.01377 -0.1119 0.9436 0.0077
-10.750 -0.6357 0.01765 0.01278 -0.1125 0.9357 0.0078
-10.500 -0.6085 0.01652 0.01156 -0.1137 0.9253 0.0081
-10.250 -0.5685 0.01537 0.01033 -0.1175 0.9177 0.0085
-10.000 -0.5172 0.01455 0.00945 -0.1232 0.9082 0.0092
-9.750 -0.4534 0.01379 0.00858 -0.1316 0.8953 0.0100
-9.500 -0.4035 0.01306 0.00769 -0.1371 0.8704 0.0110
-9.000 -0.3573 0.01243 0.00676 -0.1361 0.8149 0.0135
-8.750 -0.3378 0.01217 0.00639 -0.1348 0.7935 0.0148
-8.500 -0.3184 0.01188 0.00601 -0.1334 0.7746 0.0171
-8.250 -0.2979 0.01161 0.00567 -0.1322 0.7574 0.0202
-8.000 -0.2767 0.01136 0.00537 -0.1311 0.7412 0.0242
-7.750 -0.2548 0.01112 0.00508 -0.1302 0.7262 0.0291
-7.500 -0.2322 0.01090 0.00481 -0.1293 0.7123 0.0343
-7.250 -0.2093 0.01069 0.00456 -0.1286 0.6993 0.0398
-6.750 -0.1618 0.01026 0.00408 -0.1273 0.6755 0.0541
-6.500 -0.1378 0.01005 0.00386 -0.1267 0.6646 0.0644
-6.250 -0.1138 0.00985 0.00365 -0.1261 0.6534 0.0769
-6.000 -0.0890 0.00962 0.00344 -0.1256 0.6432 0.0927
-5.750 -0.0647 0.00939 0.00324 -0.1251 0.6331 0.1118
-5.500 -0.0398 0.00913 0.00304 -0.1247 0.6238 0.1369
-5.250 -0.0155 0.00882 0.00283 -0.1243 0.6152 0.1725
-5.000 0.0088 0.00842 0.00259 -0.1239 0.6065 0.2249
-4.750 0.0329 0.00805 0.00240 -0.1235 0.5983 0.2874
-4.500 0.0589 0.00787 0.00230 -0.1233 0.5900 0.3258
-4.250 0.0852 0.00780 0.00225 -0.1230 0.5819 0.3512
-4.000 0.1124 0.00776 0.00220 -0.1229 0.5744 0.3686
-3.750 0.1389 0.00777 0.00217 -0.1226 0.5669 0.3822
-3.500 0.1667 0.00775 0.00215 -0.1225 0.5606 0.3947
-3.250 0.1938 0.00779 0.00214 -0.1224 0.5537 0.4058
-3.000 0.2210 0.00780 0.00213 -0.1222 0.5472 0.4139
-2.750 0.2487 0.00783 0.00212 -0.1221 0.5409 0.4215
-2.500 0.2754 0.00788 0.00211 -0.1219 0.5344 0.4276
-2.250 0.3031 0.00789 0.00211 -0.1218 0.5293 0.4341
-2.000 0.3307 0.00794 0.00211 -0.1217 0.5239 0.4401
-1.750 0.3573 0.00798 0.00213 -0.1215 0.5184 0.4469
-1.500 0.3849 0.00803 0.00216 -0.1214 0.5137 0.4549
-1.250 0.4124 0.00807 0.00217 -0.1213 0.5089 0.4612
-1.000 0.4391 0.00810 0.00219 -0.1211 0.5038 0.4663
-0.750 0.4658 0.00817 0.00222 -0.1209 0.4992 0.4705
-0.500 0.4937 0.00820 0.00223 -0.1209 0.4956 0.4744
-0.250 0.5209 0.00823 0.00224 -0.1207 0.4916 0.4782
0.000 0.5474 0.00827 0.00227 -0.1205 0.4873 0.4825
0.250 0.5736 0.00835 0.00232 -0.1202 0.4828 0.4867
0.500 0.6013 0.00838 0.00235 -0.1202 0.4798 0.4908
0.750 0.6285 0.00843 0.00239 -0.1200 0.4763 0.4943
1.000 0.6550 0.00846 0.00243 -0.1198 0.4728 0.4990
1.250 0.6809 0.00854 0.00249 -0.1195 0.4692 0.5034
1.500 0.7070 0.00862 0.00256 -0.1192 0.4657 0.5080
1.750 0.7340 0.00866 0.00260 -0.1190 0.4631 0.5120
2.000 0.7602 0.00868 0.00265 -0.1187 0.4599 0.5171
2.250 0.7858 0.00874 0.00272 -0.1183 0.4567 0.5221
2.500 0.8110 0.00883 0.00279 -0.1178 0.4535 0.5272
2.750 0.8359 0.00895 0.00289 -0.1173 0.4499 0.5325
3.000 0.8621 0.00897 0.00296 -0.1170 0.4479 0.5383
3.250 0.8882 0.00901 0.00303 -0.1167 0.4453 0.5442
3.500 0.9137 0.00907 0.00311 -0.1163 0.4423 0.5502
3.750 0.9387 0.00914 0.00321 -0.1158 0.4394 0.5573
4.000 0.9631 0.00926 0.00332 -0.1153 0.4364 0.5643
4.250 0.9877 0.00938 0.00347 -0.1147 0.4333 0.5722
4.500 1.0134 0.00944 0.00357 -0.1144 0.4313 0.5805
4.750 1.0387 0.00949 0.00368 -0.1140 0.4288 0.5899
5.250 1.0880 0.00966 0.00394 -0.1129 0.4234 0.6116
5.500 1.1117 0.00978 0.00409 -0.1123 0.4205 0.6235
5.750 1.1354 0.00995 0.00427 -0.1116 0.4171 0.6368
6.000 1.1603 0.00999 0.00441 -0.1112 0.4150 0.6525
6.250 1.1850 0.01005 0.00456 -0.1107 0.4126 0.6704
6.500 1.2088 0.01012 0.00470 -0.1100 0.4095 0.6910
6.750 1.2311 0.01022 0.00488 -0.1091 0.4059 0.7149
7.000 1.2518 0.01039 0.00510 -0.1079 0.4012 0.7432
7.250 1.2748 0.01038 0.00525 -0.1071 0.3982 0.7813
7.500 1.2949 0.01033 0.00542 -0.1056 0.3943 0.8487
7.750 1.3209 0.01028 0.00558 -0.1055 0.3895 1.0000
8.000 1.3419 0.01051 0.00579 -0.1044 0.3847 1.0000
8.250 1.3662 0.01061 0.00594 -0.1039 0.3810 1.0000
8.500 1.3886 0.01077 0.00612 -0.1031 0.3768 1.0000
8.750 1.4087 0.01100 0.00634 -0.1019 0.3721 1.0000
9.000 1.4297 0.01121 0.00657 -0.1009 0.3679 1.0000
9.250 1.4524 0.01138 0.00676 -0.1002 0.3635 1.0000
9.500 1.4725 0.01161 0.00700 -0.0991 0.3580 1.0000
9.750 1.4911 0.01190 0.00729 -0.0977 0.3530 1.0000
10.000 1.5123 0.01210 0.00754 -0.0968 0.3472 1.0000
10.250 1.5295 0.01244 0.00786 -0.0952 0.3403 1.0000
10.500 1.5484 0.01273 0.00817 -0.0939 0.3330 1.0000
10.750 1.5629 0.01316 0.00858 -0.0920 0.3239 1.0000
11.000 1.5804 0.01351 0.00895 -0.0906 0.3154 1.0000
11.250 1.5933 0.01403 0.00945 -0.0885 0.3058 1.0000
11.500 1.6037 0.01467 0.01005 -0.0861 0.2927 1.0000
11.750 1.6121 0.01542 0.01076 -0.0835 0.2777 1.0000
12.000 1.6169 0.01635 0.01163 -0.0805 0.2598 1.0000
12.250 1.6171 0.01755 0.01274 -0.0770 0.2395 1.0000
12.500 1.6128 0.01906 0.01416 -0.0733 0.2198 1.0000
12.750 1.6077 0.02074 0.01576 -0.0698 0.2014 1.0000
13.000 1.6009 0.02266 0.01761 -0.0664 0.1832 1.0000
13.250 1.5956 0.02465 0.01956 -0.0636 0.1687 1.0000
13.500 1.5889 0.02689 0.02176 -0.0610 0.1551 1.0000
13.750 1.5812 0.02938 0.02422 -0.0586 0.1421 1.0000
14.000 1.5747 0.03194 0.02677 -0.0567 0.1321 1.0000
14.250 1.5669 0.03475 0.02956 -0.0550 0.1215 1.0000
14.500 1.5625 0.03741 0.03224 -0.0537 0.1137 1.0000
14.750 1.5543 0.04052 0.03536 -0.0524 0.1055 1.0000
15.000 1.5468 0.04370 0.03854 -0.0515 0.0979 1.0000
15.250 1.5417 0.04675 0.04164 -0.0507 0.0926 1.0000
15.500 1.5331 0.05026 0.04516 -0.0501 0.0858 1.0000
15.750 1.5281 0.05348 0.04842 -0.0497 0.0812 1.0000
16.000 1.5212 0.05699 0.05195 -0.0494 0.0758 1.0000
16.250 1.5148 0.06054 0.05554 -0.0493 0.0713 1.0000
16.500 1.5099 0.06399 0.05902 -0.0493 0.0668 1.0000
16.750 1.5021 0.06784 0.06288 -0.0494 0.0620 1.0000
17.000 1.4991 0.07120 0.06630 -0.0496 0.0584 1.0000
17.250 1.4918 0.07516 0.07027 -0.0500 0.0544 1.0000
17.500 1.4887 0.07863 0.07380 -0.0504 0.0511 1.0000
17.750 1.4850 0.08223 0.07743 -0.0510 0.0479 1.0000
18.000 1.4797 0.08613 0.08136 -0.0516 0.0444 1.0000
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Polar data table (+)
Polar graphs
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