EPPLER 656 AIRFOIL (e656-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 656 AIRFOIL (e656-il) Reynolds number: 1,000,000 Max Cl/Cd: 147.9 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e656-il-1000000-n5.txt Download as CSV file: xf-e656-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 656 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.3839 0.06343 0.05993 -0.1211 0.7060 0.0037
-13.250 -0.4324 0.05002 0.04635 -0.1296 0.7046 0.0036
-13.000 -0.4650 0.04098 0.03709 -0.1364 0.7025 0.0036
-12.750 -0.4806 0.03653 0.03250 -0.1387 0.7002 0.0036
-12.500 -0.4919 0.03337 0.02920 -0.1392 0.6977 0.0036
-12.250 -0.5019 0.03079 0.02647 -0.1386 0.6954 0.0036
-12.000 -0.5137 0.02836 0.02386 -0.1369 0.6929 0.0036
-11.750 -0.5167 0.02671 0.02207 -0.1350 0.6909 0.0036
-11.500 -0.5189 0.02520 0.02045 -0.1326 0.6893 0.0036
-11.250 -0.5217 0.02390 0.01902 -0.1295 0.6875 0.0036
-11.000 -0.5206 0.02280 0.01778 -0.1266 0.6855 0.0036
-10.750 -0.5092 0.02187 0.01674 -0.1250 0.6835 0.0036
-10.500 -0.4978 0.02079 0.01551 -0.1233 0.6816 0.0036
-10.250 -0.4830 0.01987 0.01446 -0.1221 0.6799 0.0036
-10.000 -0.4663 0.01903 0.01349 -0.1210 0.6782 0.0036
-9.750 -0.4482 0.01823 0.01257 -0.1200 0.6765 0.0036
-9.500 -0.4290 0.01749 0.01171 -0.1191 0.6748 0.0037
-9.250 -0.4085 0.01678 0.01090 -0.1184 0.6735 0.0037
-9.000 -0.3870 0.01610 0.01013 -0.1178 0.6724 0.0037
-8.750 -0.3641 0.01555 0.00951 -0.1174 0.6713 0.0037
-8.500 -0.3409 0.01500 0.00889 -0.1170 0.6699 0.0037
-8.250 -0.3174 0.01445 0.00827 -0.1166 0.6685 0.0038
-8.000 -0.2932 0.01397 0.00771 -0.1163 0.6669 0.0038
-7.750 -0.2684 0.01353 0.00721 -0.1160 0.6654 0.0038
-7.500 -0.2432 0.01313 0.00675 -0.1158 0.6640 0.0038
-7.250 -0.2177 0.01273 0.00630 -0.1157 0.6627 0.0039
-7.000 -0.1918 0.01239 0.00591 -0.1156 0.6613 0.0039
-6.750 -0.1660 0.01202 0.00548 -0.1155 0.6600 0.0040
-6.500 -0.1401 0.01165 0.00505 -0.1154 0.6585 0.0041
-6.250 -0.1136 0.01135 0.00470 -0.1153 0.6569 0.0044
-6.000 -0.0865 0.01108 0.00441 -0.1154 0.6558 0.0046
-5.750 -0.0590 0.01085 0.00416 -0.1155 0.6548 0.0049
-5.500 -0.0315 0.01062 0.00392 -0.1156 0.6537 0.0054
-5.250 -0.0037 0.01043 0.00371 -0.1158 0.6526 0.0057
-5.000 0.0241 0.01021 0.00348 -0.1160 0.6514 0.0066
-4.750 0.0520 0.01002 0.00329 -0.1161 0.6501 0.0081
-4.500 0.0799 0.00984 0.00311 -0.1163 0.6487 0.0104
-4.250 0.1079 0.00966 0.00294 -0.1165 0.6472 0.0144
-4.000 0.1359 0.00949 0.00279 -0.1168 0.6459 0.0205
-3.750 0.1641 0.00933 0.00266 -0.1170 0.6447 0.0281
-3.500 0.1923 0.00918 0.00254 -0.1173 0.6433 0.0377
-3.250 0.2204 0.00903 0.00243 -0.1176 0.6418 0.0519
-3.000 0.2482 0.00879 0.00231 -0.1179 0.6401 0.0856
-2.750 0.2762 0.00851 0.00221 -0.1183 0.6391 0.1295
-2.500 0.3046 0.00826 0.00215 -0.1187 0.6381 0.1807
-2.250 0.3336 0.00817 0.00211 -0.1191 0.6369 0.2050
-2.000 0.3627 0.00813 0.00207 -0.1195 0.6356 0.2139
-1.750 0.3918 0.00806 0.00202 -0.1199 0.6341 0.2235
-1.500 0.4208 0.00800 0.00197 -0.1203 0.6327 0.2324
-1.250 0.4498 0.00793 0.00193 -0.1207 0.6311 0.2418
-1.000 0.4786 0.00781 0.00188 -0.1211 0.6295 0.2639
-0.750 0.5073 0.00755 0.00185 -0.1217 0.6277 0.3503
-0.500 0.5360 0.00734 0.00183 -0.1223 0.6259 0.4172
-0.250 0.5648 0.00721 0.00182 -0.1228 0.6236 0.4699
0.000 0.5941 0.00704 0.00182 -0.1233 0.6218 0.5276
0.250 0.6234 0.00684 0.00183 -0.1240 0.6199 0.5981
0.500 0.6526 0.00673 0.00186 -0.1245 0.6178 0.6439
0.750 0.6817 0.00669 0.00189 -0.1249 0.6154 0.6738
1.000 0.7105 0.00667 0.00193 -0.1252 0.6128 0.6985
1.250 0.7391 0.00668 0.00197 -0.1255 0.6101 0.7171
1.500 0.7674 0.00672 0.00202 -0.1258 0.6072 0.7312
1.750 0.7964 0.00674 0.00207 -0.1262 0.6047 0.7426
2.000 0.8252 0.00676 0.00213 -0.1265 0.6015 0.7530
2.250 0.8537 0.00680 0.00218 -0.1268 0.5977 0.7626
2.500 0.8816 0.00685 0.00224 -0.1270 0.5937 0.7738
2.750 0.9095 0.00691 0.00230 -0.1271 0.5900 0.7825
3.000 0.9379 0.00695 0.00238 -0.1274 0.5859 0.7886
3.250 0.9660 0.00701 0.00244 -0.1277 0.5811 0.7934
3.500 0.9933 0.00710 0.00250 -0.1278 0.5760 0.7975
3.750 1.0209 0.00715 0.00259 -0.1279 0.5705 0.8019
4.000 1.0478 0.00724 0.00267 -0.1279 0.5633 0.8063
4.250 1.0744 0.00734 0.00277 -0.1279 0.5555 0.8104
4.500 1.1002 0.00748 0.00287 -0.1278 0.5451 0.8140
4.750 1.1255 0.00761 0.00299 -0.1275 0.5333 0.8174
5.000 1.1493 0.00780 0.00315 -0.1270 0.5197 0.8208
5.250 1.1719 0.00803 0.00334 -0.1262 0.5036 0.8243
5.500 1.1933 0.00831 0.00356 -0.1253 0.4859 0.8279
5.750 1.2127 0.00866 0.00382 -0.1239 0.4658 0.8312
6.000 1.2305 0.00904 0.00411 -0.1223 0.4457 0.8344
6.250 1.2468 0.00942 0.00444 -0.1205 0.4254 0.8377
6.500 1.2614 0.00982 0.00477 -0.1183 0.4063 0.8409
6.750 1.2709 0.01023 0.00512 -0.1151 0.3874 0.8445
7.000 1.2797 0.01072 0.00554 -0.1118 0.3690 0.8480
7.250 1.2881 0.01124 0.00600 -0.1086 0.3517 0.8513
7.500 1.2943 0.01184 0.00655 -0.1052 0.3339 0.8558
7.750 1.3017 0.01246 0.00713 -0.1021 0.3183 0.8604
8.000 1.3068 0.01323 0.00784 -0.0988 0.3013 0.8645
8.250 1.3112 0.01409 0.00866 -0.0957 0.2849 0.8684
8.500 1.3189 0.01489 0.00945 -0.0931 0.2725 0.8729
8.750 1.3252 0.01583 0.01037 -0.0905 0.2593 0.8781
9.000 1.3318 0.01685 0.01135 -0.0882 0.2467 0.8824
9.250 1.3370 0.01794 0.01244 -0.0857 0.2337 0.8886
9.500 1.3423 0.01912 0.01358 -0.0834 0.2199 0.8946
9.750 1.3496 0.02018 0.01465 -0.0814 0.2087 0.9033
10.000 1.3555 0.02135 0.01582 -0.0792 0.1972 0.9139
10.250 1.3602 0.02255 0.01703 -0.0769 0.1858 0.9279
10.500 1.3676 0.02383 0.01833 -0.0755 0.1723 0.9653
11.000 1.3828 0.02647 0.02091 -0.0726 0.1499 1.0000
11.250 1.3904 0.02785 0.02226 -0.0713 0.1400 1.0000
11.500 1.3979 0.02927 0.02364 -0.0700 0.1303 1.0000
11.750 1.4046 0.03077 0.02511 -0.0687 0.1200 1.0000
12.000 1.4124 0.03223 0.02653 -0.0675 0.1100 1.0000
12.250 1.4203 0.03374 0.02802 -0.0664 0.1020 1.0000
12.500 1.4282 0.03526 0.02951 -0.0654 0.0942 1.0000
12.750 1.4356 0.03685 0.03109 -0.0644 0.0864 1.0000
13.000 1.4445 0.03836 0.03260 -0.0636 0.0802 1.0000
13.250 1.4523 0.03999 0.03421 -0.0627 0.0738 1.0000
13.500 1.4601 0.04167 0.03590 -0.0619 0.0680 1.0000
13.750 1.4677 0.04338 0.03759 -0.0612 0.0617 1.0000
14.000 1.4745 0.04520 0.03941 -0.0604 0.0565 1.0000
14.250 1.4814 0.04705 0.04126 -0.0598 0.0514 1.0000
14.500 1.4878 0.04897 0.04317 -0.0592 0.0454 1.0000
14.750 1.4942 0.05096 0.04518 -0.0586 0.0415 1.0000
15.000 1.4995 0.05306 0.04727 -0.0581 0.0365 1.0000
15.250 1.5049 0.05522 0.04944 -0.0577 0.0326 1.0000
15.750 1.5177 0.05943 0.05371 -0.0571 0.0271 1.0000
16.000 1.5198 0.06207 0.05636 -0.0568 0.0228 1.0000
16.250 1.5240 0.06451 0.05881 -0.0566 0.0198 1.0000
16.500 1.5278 0.06707 0.06141 -0.0565 0.0181 1.0000
16.750 1.5340 0.06938 0.06377 -0.0565 0.0168 1.0000
17.000 1.5364 0.07218 0.06661 -0.0566 0.0149 1.0000
17.250 1.5410 0.07475 0.06923 -0.0567 0.0136 1.0000
17.500 1.5432 0.07767 0.07220 -0.0569 0.0125 1.0000
17.750 1.5475 0.08036 0.07495 -0.0572 0.0117 1.0000
18.000 1.5488 0.08350 0.07815 -0.0576 0.0107 1.0000
18.250 1.5513 0.08650 0.08121 -0.0581 0.0097 1.0000
18.500 1.5523 0.08976 0.08454 -0.0587 0.0090 1.0000
18.750 1.5532 0.09307 0.08792 -0.0594 0.0085 1.0000
19.000 1.5539 0.09644 0.09136 -0.0601 0.0077 1.0000
19.250 1.5534 0.10005 0.09504 -0.0611 0.0071 1.0000
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Polar data table (+)
Polar graphs
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