EPPLER 655 AIRFOIL (e655-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 655 AIRFOIL (e655-il) Reynolds number: 1,000,000 Max Cl/Cd: 135.13 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e655-il-1000000-n5.txt Download as CSV file: xf-e655-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 655 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
------ -------- --------- --------- -------- -------- --------
-17.250 -0.6285 0.08028 0.07657 -0.1069 0.7880 0.0039
-17.000 -0.6756 0.06890 0.06501 -0.1134 0.7830 0.0040
-16.500 -0.7273 0.05386 0.04960 -0.1223 0.7704 0.0039
-16.250 -0.7430 0.04844 0.04403 -0.1254 0.7635 0.0040
-16.000 -0.7524 0.04430 0.03973 -0.1275 0.7570 0.0038
-15.750 -0.7613 0.04058 0.03589 -0.1290 0.7511 0.0039
-15.500 -0.7683 0.03746 0.03263 -0.1298 0.7450 0.0040
-15.250 -0.7700 0.03506 0.03012 -0.1301 0.7403 0.0039
-15.000 -0.7703 0.03292 0.02787 -0.1301 0.7359 0.0039
-14.750 -0.7702 0.03094 0.02580 -0.1297 0.7314 0.0039
-14.500 -0.7677 0.02928 0.02404 -0.1291 0.7271 0.0040
-14.250 -0.7636 0.02780 0.02246 -0.1284 0.7236 0.0040
-14.000 -0.7581 0.02645 0.02103 -0.1275 0.7203 0.0040
-13.750 -0.7519 0.02521 0.01971 -0.1265 0.7168 0.0041
-13.500 -0.7440 0.02413 0.01855 -0.1254 0.7134 0.0042
-13.250 -0.7360 0.02310 0.01743 -0.1242 0.7100 0.0042
-13.000 -0.7262 0.02219 0.01645 -0.1230 0.7071 0.0042
-12.750 -0.7154 0.02134 0.01553 -0.1217 0.7043 0.0042
-12.500 -0.7056 0.02046 0.01458 -0.1202 0.7015 0.0044
-12.250 -0.6934 0.01976 0.01382 -0.1189 0.6988 0.0045
-12.000 -0.6813 0.01908 0.01306 -0.1174 0.6963 0.0045
-11.750 -0.6696 0.01842 0.01234 -0.1157 0.6938 0.0047
-11.500 -0.6572 0.01787 0.01172 -0.1140 0.6915 0.0048
-11.250 -0.6466 0.01735 0.01115 -0.1118 0.6898 0.0047
-11.000 -0.6314 0.01690 0.01065 -0.1103 0.6879 0.0049
-10.750 -0.6132 0.01644 0.01013 -0.1092 0.6860 0.0050
-10.500 -0.5939 0.01600 0.00965 -0.1083 0.6839 0.0051
-10.250 -0.5749 0.01549 0.00908 -0.1073 0.6818 0.0054
-10.000 -0.5543 0.01507 0.00862 -0.1065 0.6797 0.0057
-9.750 -0.5327 0.01469 0.00820 -0.1059 0.6777 0.0060
-9.500 -0.5103 0.01435 0.00780 -0.1053 0.6757 0.0063
-9.250 -0.4871 0.01401 0.00743 -0.1048 0.6743 0.0067
-9.000 -0.4633 0.01368 0.00707 -0.1045 0.6730 0.0070
-8.750 -0.4396 0.01332 0.00670 -0.1041 0.6716 0.0077
-8.500 -0.4151 0.01301 0.00637 -0.1038 0.6700 0.0083
-8.250 -0.3901 0.01273 0.00606 -0.1036 0.6684 0.0090
-8.000 -0.3652 0.01244 0.00576 -0.1034 0.6668 0.0101
-7.750 -0.3398 0.01218 0.00548 -0.1032 0.6650 0.0113
-7.500 -0.3142 0.01193 0.00521 -0.1031 0.6633 0.0126
-7.250 -0.2883 0.01171 0.00497 -0.1030 0.6617 0.0143
-7.000 -0.2623 0.01148 0.00472 -0.1029 0.6601 0.0159
-6.750 -0.2358 0.01128 0.00451 -0.1029 0.6586 0.0180
-6.500 -0.2091 0.01105 0.00429 -0.1030 0.6576 0.0204
-6.250 -0.1821 0.01083 0.00408 -0.1031 0.6564 0.0233
-6.000 -0.1551 0.01061 0.00389 -0.1032 0.6549 0.0273
-5.750 -0.1280 0.01039 0.00369 -0.1033 0.6534 0.0330
-5.500 -0.1007 0.01019 0.00351 -0.1034 0.6519 0.0393
-5.250 -0.0734 0.00998 0.00334 -0.1036 0.6505 0.0483
-5.000 -0.0460 0.00977 0.00317 -0.1037 0.6491 0.0593
-4.750 -0.0186 0.00956 0.00301 -0.1039 0.6475 0.0721
-4.500 0.0091 0.00938 0.00287 -0.1041 0.6460 0.0860
-4.250 0.0368 0.00920 0.00274 -0.1043 0.6443 0.1022
-4.000 0.0647 0.00905 0.00262 -0.1046 0.6427 0.1195
-3.750 0.0929 0.00884 0.00251 -0.1049 0.6417 0.1415
-3.500 0.1211 0.00863 0.00240 -0.1053 0.6405 0.1698
-3.250 0.1495 0.00842 0.00230 -0.1057 0.6391 0.2003
-3.000 0.1780 0.00823 0.00220 -0.1061 0.6376 0.2312
-2.750 0.2066 0.00801 0.00212 -0.1066 0.6361 0.2689
-2.500 0.2352 0.00781 0.00204 -0.1070 0.6345 0.3092
-2.250 0.2640 0.00761 0.00196 -0.1075 0.6329 0.3518
-2.000 0.2928 0.00740 0.00189 -0.1080 0.6312 0.4007
-1.750 0.3217 0.00719 0.00182 -0.1086 0.6296 0.4520
-1.500 0.3507 0.00699 0.00177 -0.1091 0.6278 0.5068
-1.250 0.3800 0.00682 0.00175 -0.1097 0.6262 0.5592
-1.000 0.4095 0.00671 0.00177 -0.1102 0.6248 0.5998
-0.750 0.4390 0.00667 0.00179 -0.1107 0.6230 0.6256
-0.500 0.4685 0.00665 0.00181 -0.1112 0.6209 0.6432
-0.250 0.4979 0.00666 0.00183 -0.1116 0.6186 0.6557
0.000 0.5272 0.00667 0.00184 -0.1120 0.6159 0.6662
0.250 0.5562 0.00670 0.00186 -0.1123 0.6132 0.6740
0.500 0.5852 0.00674 0.00189 -0.1127 0.6106 0.6817
0.750 0.6146 0.00676 0.00192 -0.1131 0.6083 0.6882
1.000 0.6439 0.00677 0.00197 -0.1135 0.6056 0.6948
1.250 0.6730 0.00681 0.00200 -0.1139 0.6025 0.7009
1.500 0.7018 0.00684 0.00203 -0.1142 0.5993 0.7058
1.750 0.7302 0.00689 0.00207 -0.1145 0.5959 0.7108
2.000 0.7593 0.00692 0.00212 -0.1149 0.5926 0.7162
2.250 0.7883 0.00696 0.00217 -0.1153 0.5886 0.7207
2.500 0.8165 0.00700 0.00222 -0.1155 0.5842 0.7244
2.750 0.8444 0.00706 0.00227 -0.1157 0.5798 0.7277
3.000 0.8731 0.00710 0.00233 -0.1160 0.5749 0.7308
3.250 0.9010 0.00717 0.00239 -0.1162 0.5687 0.7338
3.500 0.9287 0.00725 0.00246 -0.1163 0.5627 0.7365
3.750 0.9563 0.00732 0.00253 -0.1165 0.5552 0.7391
4.000 0.9830 0.00741 0.00262 -0.1165 0.5472 0.7416
4.250 1.0093 0.00753 0.00272 -0.1164 0.5367 0.7441
4.500 1.0351 0.00766 0.00284 -0.1162 0.5251 0.7469
4.750 1.0598 0.00785 0.00298 -0.1158 0.5112 0.7496
5.000 1.0834 0.00807 0.00314 -0.1153 0.4952 0.7522
5.250 1.1056 0.00835 0.00334 -0.1144 0.4770 0.7544
5.500 1.1260 0.00866 0.00359 -0.1133 0.4576 0.7569
5.750 1.1458 0.00899 0.00386 -0.1121 0.4374 0.7598
6.000 1.1641 0.00936 0.00415 -0.1106 0.4167 0.7629
6.250 1.1810 0.00975 0.00447 -0.1088 0.3973 0.7659
6.500 1.1959 0.01014 0.00479 -0.1067 0.3793 0.7688
6.750 1.2064 0.01055 0.00512 -0.1037 0.3609 0.7717
7.000 1.2175 0.01099 0.00552 -0.1009 0.3440 0.7748
7.250 1.2282 0.01147 0.00595 -0.0982 0.3278 0.7784
7.500 1.2385 0.01199 0.00643 -0.0954 0.3125 0.7823
7.750 1.2474 0.01259 0.00697 -0.0926 0.2967 0.7862
8.000 1.2552 0.01327 0.00760 -0.0898 0.2810 0.7897
8.250 1.2633 0.01398 0.00829 -0.0871 0.2676 0.7935
8.500 1.2706 0.01480 0.00908 -0.0845 0.2533 0.7977
8.750 1.2791 0.01565 0.00990 -0.0822 0.2404 0.8020
9.000 1.2871 0.01658 0.01080 -0.0800 0.2276 0.8061
9.250 1.2946 0.01758 0.01179 -0.0779 0.2151 0.8109
9.500 1.3024 0.01863 0.01282 -0.0759 0.2037 0.8160
9.750 1.3091 0.01980 0.01395 -0.0739 0.1911 0.8209
10.000 1.3172 0.02091 0.01506 -0.0721 0.1799 0.8256
10.250 1.3261 0.02201 0.01615 -0.0705 0.1700 0.8310
10.500 1.3328 0.02329 0.01740 -0.0687 0.1582 0.8366
10.750 1.3397 0.02456 0.01866 -0.0670 0.1477 0.8422
11.000 1.3472 0.02582 0.01992 -0.0655 0.1378 0.8489
11.500 1.3629 0.02838 0.02248 -0.0626 0.1209 0.8641
11.750 1.3714 0.02965 0.02377 -0.0613 0.1129 0.8728
12.000 1.3791 0.03097 0.02511 -0.0600 0.1055 0.8834
12.250 1.3848 0.03244 0.02658 -0.0585 0.0970 0.8968
13.250 1.4180 0.03825 0.03249 -0.0547 0.0706 1.0000
13.500 1.4262 0.03988 0.03413 -0.0540 0.0657 1.0000
13.750 1.4349 0.04148 0.03572 -0.0533 0.0606 1.0000
14.000 1.4399 0.04344 0.03766 -0.0525 0.0541 1.0000
14.250 1.4490 0.04507 0.03930 -0.0520 0.0500 1.0000
14.500 1.4560 0.04694 0.04118 -0.0514 0.0461 1.0000
14.750 1.4625 0.04888 0.04312 -0.0509 0.0413 1.0000
15.000 1.4691 0.05084 0.04509 -0.0505 0.0376 1.0000
15.250 1.4721 0.05322 0.04745 -0.0500 0.0324 1.0000
15.500 1.4811 0.05501 0.04928 -0.0497 0.0309 1.0000
16.000 1.4901 0.05966 0.05396 -0.0492 0.0241 1.0000
16.250 1.4965 0.06186 0.05620 -0.0491 0.0232 1.0000
16.500 1.5021 0.06417 0.05854 -0.0490 0.0214 1.0000
16.750 1.5046 0.06689 0.06129 -0.0490 0.0189 1.0000
17.000 1.5107 0.06923 0.06368 -0.0491 0.0180 1.0000
17.250 1.5143 0.07190 0.06639 -0.0493 0.0164 1.0000
17.500 1.5169 0.07471 0.06924 -0.0495 0.0150 1.0000
17.750 1.5207 0.07746 0.07206 -0.0498 0.0142 1.0000
18.000 1.5238 0.08030 0.07495 -0.0502 0.0132 1.0000
18.250 1.5250 0.08348 0.07819 -0.0507 0.0124 1.0000
18.500 1.5277 0.08647 0.08125 -0.0513 0.0116 1.0000
18.750 1.5292 0.08967 0.08450 -0.0519 0.0110 1.0000
19.000 1.5288 0.09317 0.08807 -0.0527 0.0103 1.0000
19.250 1.5294 0.09657 0.09153 -0.0536 0.0096 1.0000
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