EPPLER 656 AIRFOIL (e656-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 656 AIRFOIL (e656-il) Reynolds number: 500,000 Max Cl/Cd: 118.92 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e656-il-500000-n5.txt Download as CSV file: xf-e656-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.1370 0.09229 0.08839 -0.1087 0.7218 0.0058
-12.000 -0.3227 0.05132 0.04723 -0.1287 0.7224 0.0053
-11.750 -0.3481 0.04352 0.03924 -0.1348 0.7200 0.0052
-11.500 -0.3702 0.03859 0.03412 -0.1372 0.7173 0.0052
-11.250 -0.3883 0.03505 0.03038 -0.1372 0.7148 0.0052
-11.000 -0.4035 0.03220 0.02729 -0.1358 0.7124 0.0052
-10.750 -0.4089 0.03034 0.02525 -0.1338 0.7101 0.0052
-10.500 -0.4182 0.02838 0.02308 -0.1308 0.7080 0.0052
-10.250 -0.4208 0.02696 0.02148 -0.1278 0.7059 0.0052
-10.000 -0.4152 0.02546 0.01979 -0.1259 0.7037 0.0052
-9.750 -0.4057 0.02408 0.01820 -0.1242 0.7015 0.0052
-9.500 -0.3930 0.02283 0.01676 -0.1228 0.6996 0.0052
-9.250 -0.3777 0.02171 0.01546 -0.1216 0.6978 0.0053
-9.000 -0.3607 0.02067 0.01425 -0.1205 0.6961 0.0053
-8.750 -0.3416 0.01983 0.01326 -0.1197 0.6945 0.0053
-8.500 -0.3215 0.01903 0.01232 -0.1190 0.6929 0.0054
-8.250 -0.3008 0.01825 0.01140 -0.1183 0.6913 0.0055
-8.000 -0.2789 0.01755 0.01060 -0.1177 0.6900 0.0056
-7.750 -0.2562 0.01692 0.00989 -0.1172 0.6885 0.0057
-7.500 -0.2329 0.01634 0.00923 -0.1168 0.6867 0.0057
-7.250 -0.2093 0.01578 0.00859 -0.1164 0.6850 0.0059
-7.000 -0.1858 0.01518 0.00792 -0.1161 0.6834 0.0061
-6.750 -0.1611 0.01471 0.00740 -0.1158 0.6819 0.0063
-6.500 -0.1358 0.01431 0.00694 -0.1157 0.6805 0.0066
-6.250 -0.1100 0.01396 0.00653 -0.1156 0.6791 0.0071
-6.000 -0.0840 0.01362 0.00612 -0.1155 0.6777 0.0076
-5.750 -0.0577 0.01331 0.00575 -0.1154 0.6763 0.0081
-5.500 -0.0315 0.01300 0.00539 -0.1153 0.6747 0.0091
-5.250 -0.0047 0.01275 0.00509 -0.1154 0.6733 0.0102
-5.000 0.0221 0.01246 0.00480 -0.1154 0.6720 0.0122
-4.750 0.0490 0.01220 0.00455 -0.1154 0.6707 0.0157
-4.500 0.0761 0.01195 0.00433 -0.1155 0.6694 0.0223
-4.250 0.1032 0.01171 0.00414 -0.1157 0.6679 0.0330
-4.000 0.1304 0.01146 0.00396 -0.1158 0.6664 0.0478
-3.750 0.1576 0.01120 0.00380 -0.1160 0.6648 0.0680
-3.500 0.1849 0.01095 0.00364 -0.1162 0.6633 0.0949
-3.250 0.2123 0.01068 0.00350 -0.1165 0.6619 0.1315
-3.000 0.2398 0.01042 0.00341 -0.1168 0.6606 0.1803
-2.750 0.2683 0.01035 0.00335 -0.1171 0.6593 0.2093
-2.500 0.2969 0.01028 0.00325 -0.1174 0.6578 0.2232
-2.250 0.3253 0.01018 0.00316 -0.1178 0.6563 0.2369
-2.000 0.3533 0.00998 0.00309 -0.1181 0.6550 0.2628
-1.750 0.3810 0.00964 0.00305 -0.1186 0.6537 0.3530
-1.500 0.4090 0.00937 0.00300 -0.1190 0.6521 0.4253
-1.250 0.4372 0.00909 0.00297 -0.1195 0.6503 0.5057
-1.000 0.4654 0.00884 0.00298 -0.1199 0.6487 0.5862
-0.750 0.4936 0.00871 0.00301 -0.1201 0.6471 0.6414
-0.500 0.5216 0.00866 0.00308 -0.1203 0.6454 0.6863
-0.250 0.5495 0.00867 0.00316 -0.1203 0.6438 0.7211
0.000 0.5781 0.00872 0.00321 -0.1205 0.6421 0.7397
0.250 0.6069 0.00879 0.00325 -0.1208 0.6403 0.7503
0.500 0.6355 0.00884 0.00330 -0.1211 0.6384 0.7599
0.750 0.6633 0.00888 0.00337 -0.1212 0.6361 0.7674
1.000 0.6917 0.00893 0.00342 -0.1214 0.6337 0.7749
1.250 0.7200 0.00897 0.00346 -0.1217 0.6313 0.7810
1.500 0.7480 0.00902 0.00351 -0.1218 0.6289 0.7878
1.750 0.7766 0.00907 0.00354 -0.1221 0.6265 0.7965
2.000 0.8042 0.00914 0.00361 -0.1221 0.6242 0.8035
2.250 0.8318 0.00920 0.00369 -0.1222 0.6215 0.8110
2.500 0.8592 0.00925 0.00378 -0.1223 0.6183 0.8168
2.750 0.8859 0.00930 0.00386 -0.1222 0.6148 0.8218
3.000 0.9133 0.00934 0.00392 -0.1222 0.6114 0.8269
3.250 0.9413 0.00939 0.00394 -0.1225 0.6081 0.8314
3.500 0.9680 0.00944 0.00403 -0.1224 0.6043 0.8347
3.750 0.9943 0.00949 0.00413 -0.1223 0.5999 0.8381
4.000 1.0208 0.00954 0.00421 -0.1222 0.5955 0.8420
4.250 1.0476 0.00960 0.00425 -0.1222 0.5914 0.8460
4.500 1.0743 0.00968 0.00437 -0.1223 0.5863 0.8496
4.750 1.0995 0.00973 0.00447 -0.1219 0.5803 0.8524
5.000 1.1244 0.00980 0.00454 -0.1215 0.5743 0.8552
5.250 1.1492 0.00988 0.00467 -0.1212 0.5665 0.8584
5.500 1.1732 0.00998 0.00477 -0.1207 0.5582 0.8616
5.750 1.1969 0.01010 0.00490 -0.1201 0.5476 0.8650
6.000 1.2189 0.01025 0.00505 -0.1193 0.5362 0.8683
6.250 1.2382 0.01043 0.00523 -0.1178 0.5232 0.8719
6.500 1.2557 0.01068 0.00545 -0.1161 0.5079 0.8760
6.750 1.2711 0.01099 0.00571 -0.1141 0.4908 0.8802
7.000 1.2813 0.01134 0.00602 -0.1110 0.4733 0.8844
7.250 1.2867 0.01177 0.00641 -0.1071 0.4551 0.8899
7.500 1.2915 0.01234 0.00692 -0.1032 0.4364 0.8958
7.750 1.2946 0.01298 0.00752 -0.0993 0.4182 0.9019
8.000 1.2957 0.01374 0.00824 -0.0952 0.4003 0.9091
8.250 1.2978 0.01457 0.00905 -0.0916 0.3836 0.9171
8.500 1.2979 0.01553 0.00999 -0.0878 0.3668 0.9272
8.750 1.2982 0.01658 0.01103 -0.0843 0.3502 0.9422
9.000 1.3036 0.01779 0.01222 -0.0824 0.3325 1.0000
9.250 1.3082 0.01916 0.01353 -0.0803 0.3154 1.0000
9.500 1.3144 0.02048 0.01481 -0.0785 0.3002 1.0000
9.750 1.3202 0.02186 0.01614 -0.0767 0.2849 1.0000
10.000 1.3265 0.02324 0.01748 -0.0750 0.2706 1.0000
10.250 1.3325 0.02466 0.01887 -0.0734 0.2565 1.0000
10.500 1.3385 0.02612 0.02029 -0.0718 0.2433 1.0000
10.750 1.3442 0.02762 0.02175 -0.0703 0.2299 1.0000
11.000 1.3498 0.02917 0.02325 -0.0688 0.2163 1.0000
11.250 1.3554 0.03075 0.02480 -0.0674 0.2037 1.0000
11.500 1.3617 0.03232 0.02633 -0.0662 0.1902 1.0000
11.750 1.3680 0.03394 0.02792 -0.0650 0.1775 1.0000
12.000 1.3749 0.03555 0.02950 -0.0639 0.1657 1.0000
12.250 1.3816 0.03721 0.03114 -0.0628 0.1553 1.0000
12.500 1.3877 0.03895 0.03284 -0.0618 0.1445 1.0000
12.750 1.3948 0.04066 0.03453 -0.0609 0.1338 1.0000
13.000 1.4015 0.04244 0.03630 -0.0601 0.1239 1.0000
13.250 1.4082 0.04424 0.03808 -0.0593 0.1143 1.0000
13.500 1.4137 0.04620 0.04002 -0.0585 0.1056 1.0000
13.750 1.4212 0.04802 0.04185 -0.0579 0.0978 1.0000
14.000 1.4279 0.04993 0.04377 -0.0574 0.0904 1.0000
14.250 1.4332 0.05204 0.04587 -0.0568 0.0836 1.0000
14.500 1.4402 0.05400 0.04785 -0.0563 0.0770 1.0000
14.750 1.4457 0.05617 0.05003 -0.0559 0.0713 1.0000
15.000 1.4504 0.05846 0.05233 -0.0555 0.0654 1.0000
15.250 1.4561 0.06068 0.05459 -0.0553 0.0600 1.0000
15.500 1.4604 0.06308 0.05701 -0.0550 0.0549 1.0000
16.000 1.4681 0.06816 0.06214 -0.0548 0.0457 1.0000
16.250 1.4721 0.07075 0.06478 -0.0548 0.0421 1.0000
16.500 1.4743 0.07360 0.06766 -0.0548 0.0385 1.0000
16.750 1.4777 0.07635 0.07046 -0.0550 0.0351 1.0000
17.000 1.4795 0.07935 0.07351 -0.0552 0.0324 1.0000
17.250 1.4812 0.08242 0.07663 -0.0556 0.0295 1.0000
17.500 1.4831 0.08551 0.07979 -0.0560 0.0274 1.0000
17.750 1.4834 0.08887 0.08321 -0.0565 0.0252 1.0000
18.000 1.4846 0.09211 0.08653 -0.0571 0.0233 1.0000
18.500 1.4836 0.09928 0.09384 -0.0588 0.0198 1.0000
18.750 1.4828 0.10296 0.09759 -0.0597 0.0184 1.0000
19.000 1.4813 0.10679 0.10150 -0.0609 0.0168 1.0000
19.250 1.4787 0.11080 0.10558 -0.0621 0.0154 1.0000
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Polar data table (+)
Polar graphs
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