EPPLER 555 AIRFOIL (e555-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 555 AIRFOIL (e555-il) Reynolds number: 500,000 Max Cl/Cd: 93.43 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e555-il-500000.txt Download as CSV file: xf-e555-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 555 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
------ -------- --------- --------- -------- -------- --------
-14.250 -0.7308 0.07313 0.06960 -0.0668 1.0000 0.0108
-14.000 -0.7410 0.06897 0.06531 -0.0688 1.0000 0.0107
-13.750 -0.7467 0.06504 0.06133 -0.0693 1.0000 0.0105
-13.500 -0.7580 0.06088 0.05706 -0.0704 1.0000 0.0104
-13.250 -0.7708 0.05665 0.05269 -0.0714 1.0000 0.0103
-13.000 -0.7802 0.05307 0.04898 -0.0720 1.0000 0.0102
-12.750 -0.7895 0.04958 0.04534 -0.0723 1.0000 0.0101
-12.500 -0.7973 0.04638 0.04199 -0.0721 1.0000 0.0099
-12.250 -0.8022 0.04365 0.03911 -0.0716 1.0000 0.0098
-12.000 -0.8065 0.04103 0.03635 -0.0706 1.0000 0.0097
-11.750 -0.8094 0.03874 0.03391 -0.0692 1.0000 0.0096
-11.500 -0.8108 0.03678 0.03184 -0.0676 1.0000 0.0096
-11.250 -0.8120 0.03507 0.03002 -0.0656 1.0000 0.0095
-11.000 -0.8145 0.03349 0.02834 -0.0631 1.0000 0.0095
-10.750 -0.8200 0.03213 0.02692 -0.0600 1.0000 0.0095
-10.500 -0.8322 0.03098 0.02571 -0.0559 1.0000 0.0095
-10.250 -0.8188 0.02947 0.02410 -0.0562 0.9978 0.0095
-10.000 -0.7920 0.02786 0.02239 -0.0589 0.9942 0.0096
-9.750 -0.7656 0.02617 0.02061 -0.0616 0.9898 0.0098
-9.500 -0.7352 0.02445 0.01880 -0.0652 0.9857 0.0100
-9.250 -0.7040 0.02282 0.01708 -0.0687 0.9818 0.0103
-9.000 -0.6755 0.02143 0.01560 -0.0711 0.9760 0.0105
-8.750 -0.6436 0.01959 0.01369 -0.0748 0.9726 0.0111
-8.500 -0.6176 0.01838 0.01244 -0.0763 0.9657 0.0116
-8.250 -0.5836 0.01734 0.01134 -0.0789 0.9623 0.0127
-8.000 -0.5478 0.01615 0.01009 -0.0821 0.9600 0.0143
-7.750 -0.5203 0.01532 0.00922 -0.0829 0.9530 0.0169
-7.500 -0.4860 0.01429 0.00820 -0.0853 0.9495 0.0227
-7.250 -0.4495 0.01328 0.00724 -0.0881 0.9470 0.0376
-7.000 -0.4182 0.01242 0.00651 -0.0897 0.9411 0.0616
-6.750 -0.3831 0.01139 0.00572 -0.0923 0.9361 0.1091
-6.500 -0.3437 0.00972 0.00460 -0.0968 0.9327 0.2268
-6.250 -0.3090 0.00864 0.00402 -0.0995 0.9257 0.3539
-6.000 -0.2703 0.00847 0.00389 -0.1019 0.9192 0.3899
-5.750 -0.2326 0.00845 0.00382 -0.1039 0.9116 0.4102
-5.500 -0.1959 0.00843 0.00372 -0.1057 0.9026 0.4212
-5.250 -0.1621 0.00847 0.00363 -0.1068 0.8922 0.4304
-5.000 -0.1281 0.00851 0.00362 -0.1080 0.8824 0.4392
-4.750 -0.0968 0.00861 0.00357 -0.1086 0.8711 0.4469
-4.500 -0.0676 0.00861 0.00355 -0.1087 0.8595 0.4528
-4.250 -0.0377 0.00880 0.00364 -0.1090 0.8483 0.4619
-4.000 -0.0088 0.00886 0.00366 -0.1090 0.8370 0.4687
-3.750 0.0189 0.00886 0.00360 -0.1089 0.8250 0.4721
-3.500 0.0473 0.00885 0.00349 -0.1090 0.8137 0.4749
-3.250 0.0759 0.00886 0.00338 -0.1091 0.8027 0.4778
-3.000 0.1038 0.00883 0.00326 -0.1090 0.7912 0.4804
-2.750 0.1314 0.00877 0.00316 -0.1089 0.7800 0.4829
-2.500 0.1593 0.00877 0.00310 -0.1089 0.7693 0.4853
-2.250 0.1870 0.00877 0.00305 -0.1088 0.7583 0.4879
-2.000 0.2147 0.00878 0.00300 -0.1087 0.7473 0.4908
-1.750 0.2426 0.00882 0.00294 -0.1087 0.7370 0.4937
-1.500 0.2704 0.00884 0.00288 -0.1086 0.7261 0.4961
-1.250 0.2978 0.00879 0.00282 -0.1085 0.7157 0.4987
-1.000 0.3253 0.00881 0.00280 -0.1084 0.7056 0.5012
-0.750 0.3528 0.00883 0.00279 -0.1083 0.6949 0.5040
-0.500 0.3804 0.00887 0.00279 -0.1082 0.6848 0.5071
-0.250 0.4080 0.00894 0.00278 -0.1081 0.6748 0.5101
0.000 0.4355 0.00895 0.00277 -0.1080 0.6642 0.5127
0.250 0.4628 0.00895 0.00276 -0.1079 0.6543 0.5155
0.500 0.4900 0.00900 0.00278 -0.1077 0.6440 0.5183
0.750 0.5173 0.00904 0.00282 -0.1076 0.6336 0.5212
1.000 0.5446 0.00911 0.00285 -0.1074 0.6238 0.5246
1.250 0.5718 0.00919 0.00288 -0.1073 0.6132 0.5278
1.500 0.5989 0.00921 0.00291 -0.1071 0.6029 0.5310
1.750 0.6257 0.00928 0.00296 -0.1069 0.5926 0.5340
2.000 0.6526 0.00934 0.00303 -0.1067 0.5816 0.5372
2.250 0.6794 0.00942 0.00310 -0.1065 0.5706 0.5407
2.500 0.7061 0.00954 0.00316 -0.1062 0.5598 0.5442
2.750 0.7325 0.00960 0.00324 -0.1060 0.5484 0.5479
3.000 0.7590 0.00968 0.00334 -0.1057 0.5372 0.5516
3.250 0.7852 0.00979 0.00344 -0.1054 0.5263 0.5555
3.500 0.8112 0.00993 0.00355 -0.1050 0.5147 0.5595
3.750 0.8375 0.01002 0.00365 -0.1047 0.5029 0.5633
4.000 0.8634 0.01012 0.00378 -0.1044 0.4913 0.5674
4.250 0.8889 0.01027 0.00393 -0.1039 0.4797 0.5721
4.500 0.9145 0.01043 0.00406 -0.1035 0.4676 0.5770
4.750 0.9402 0.01054 0.00421 -0.1031 0.4555 0.5816
5.000 0.9654 0.01069 0.00439 -0.1027 0.4435 0.5865
5.250 0.9902 0.01088 0.00456 -0.1021 0.4312 0.5918
5.750 1.0393 0.01124 0.00496 -0.1010 0.4049 0.6030
6.000 1.0637 0.01145 0.00516 -0.1004 0.3913 0.6097
6.250 1.0875 0.01165 0.00539 -0.0997 0.3772 0.6160
6.500 1.1109 0.01189 0.00564 -0.0989 0.3625 0.6232
6.750 1.1339 0.01214 0.00590 -0.0981 0.3476 0.6304
7.000 1.1563 0.01241 0.00618 -0.0972 0.3317 0.6383
7.250 1.1780 0.01273 0.00648 -0.0962 0.3142 0.6467
7.500 1.1988 0.01307 0.00682 -0.0950 0.2959 0.6564
7.750 1.2185 0.01346 0.00719 -0.0937 0.2768 0.6663
8.000 1.2378 0.01387 0.00757 -0.0924 0.2551 0.6776
8.250 1.2544 0.01438 0.00803 -0.0905 0.2327 0.6897
8.500 1.2696 0.01486 0.00849 -0.0884 0.2117 0.7026
8.750 1.2840 0.01539 0.00899 -0.0862 0.1926 0.7173
9.000 1.2976 0.01596 0.00954 -0.0840 0.1751 0.7345
9.250 1.3107 0.01656 0.01014 -0.0816 0.1588 0.7551
9.500 1.3230 0.01715 0.01077 -0.0792 0.1439 0.7801
9.750 1.3343 0.01773 0.01142 -0.0767 0.1302 0.8141
10.000 1.3409 0.01819 0.01203 -0.0731 0.1185 0.8793
10.250 1.3493 0.01873 0.01264 -0.0701 0.1076 1.0000
10.500 1.3607 0.01956 0.01342 -0.0680 0.0969 1.0000
10.750 1.3707 0.02047 0.01429 -0.0659 0.0873 1.0000
11.000 1.3796 0.02146 0.01526 -0.0637 0.0785 1.0000
11.250 1.3899 0.02241 0.01622 -0.0617 0.0712 1.0000
11.500 1.3976 0.02354 0.01734 -0.0597 0.0645 1.0000
11.750 1.4049 0.02475 0.01855 -0.0577 0.0585 1.0000
12.000 1.4124 0.02600 0.01983 -0.0559 0.0533 1.0000
12.250 1.4171 0.02751 0.02133 -0.0540 0.0485 1.0000
12.500 1.4239 0.02893 0.02282 -0.0525 0.0445 1.0000
12.750 1.4275 0.03067 0.02457 -0.0509 0.0407 1.0000
13.000 1.4320 0.03242 0.02638 -0.0495 0.0375 1.0000
13.250 1.4360 0.03428 0.02829 -0.0483 0.0347 1.0000
13.500 1.4351 0.03667 0.03071 -0.0471 0.0322 1.0000
13.750 1.4406 0.03858 0.03271 -0.0464 0.0299 1.0000
14.000 1.4413 0.04101 0.03518 -0.0456 0.0281 1.0000
14.250 1.4379 0.04398 0.03822 -0.0450 0.0264 1.0000
14.500 1.4414 0.04635 0.04069 -0.0447 0.0248 1.0000
14.750 1.4411 0.04921 0.04362 -0.0445 0.0234 1.0000
15.000 1.4346 0.05291 0.04739 -0.0446 0.0222 1.0000
15.250 1.4349 0.05596 0.05054 -0.0448 0.0210 1.0000
15.500 1.4345 0.05918 0.05387 -0.0452 0.0200 1.0000
15.750 1.4318 0.06279 0.05755 -0.0458 0.0190 1.0000
16.000 1.4238 0.06726 0.06210 -0.0468 0.0182 1.0000
16.250 1.4169 0.07174 0.06669 -0.0480 0.0175 1.0000
16.500 1.4152 0.07559 0.07065 -0.0491 0.0167 1.0000
16.750 1.4121 0.07974 0.07490 -0.0504 0.0160 1.0000
17.000 1.4074 0.08424 0.07949 -0.0520 0.0154 1.0000
17.250 1.3978 0.08963 0.08497 -0.0540 0.0149 1.0000
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