EPPLER 655 AIRFOIL (e655-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 655 AIRFOIL (e655-il) Reynolds number: 500,000 Max Cl/Cd: 111.23 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e655-il-500000-n5.txt Download as CSV file: xf-e655-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.750 -0.4091 0.11277 0.10935 -0.0901 0.8396 0.0062
-16.500 -0.4663 0.09715 0.09351 -0.0978 0.8364 0.0062
-16.000 -0.5304 0.07808 0.07405 -0.1079 0.8178 0.0059
-15.750 -0.5576 0.06986 0.06563 -0.1125 0.8091 0.0060
-15.500 -0.5793 0.06264 0.05822 -0.1168 0.8006 0.0061
-15.000 -0.6089 0.05140 0.04662 -0.1233 0.7851 0.0059
-14.750 -0.6203 0.04691 0.04195 -0.1256 0.7778 0.0059
-14.500 -0.6286 0.04316 0.03804 -0.1273 0.7715 0.0059
-14.250 -0.6342 0.04005 0.03478 -0.1283 0.7652 0.0060
-14.000 -0.6380 0.03738 0.03196 -0.1287 0.7598 0.0060
-13.750 -0.6396 0.03506 0.02951 -0.1288 0.7552 0.0061
-13.500 -0.6391 0.03306 0.02739 -0.1285 0.7505 0.0062
-13.250 -0.6384 0.03121 0.02541 -0.1279 0.7459 0.0063
-12.750 -0.6305 0.02820 0.02217 -0.1263 0.7385 0.0063
-12.500 -0.6258 0.02682 0.02067 -0.1252 0.7347 0.0066
-12.250 -0.6183 0.02567 0.01940 -0.1240 0.7311 0.0068
-12.000 -0.6106 0.02460 0.01822 -0.1227 0.7276 0.0068
-11.750 -0.6016 0.02363 0.01712 -0.1214 0.7245 0.0070
-11.500 -0.5930 0.02263 0.01606 -0.1199 0.7216 0.0071
-11.250 -0.5834 0.02172 0.01508 -0.1184 0.7187 0.0071
-11.000 -0.5733 0.02089 0.01418 -0.1167 0.7159 0.0075
-10.750 -0.5618 0.02020 0.01342 -0.1150 0.7133 0.0077
-10.500 -0.5511 0.01963 0.01276 -0.1130 0.7109 0.0079
-10.250 -0.5380 0.01911 0.01215 -0.1113 0.7087 0.0082
-10.000 -0.5209 0.01857 0.01154 -0.1102 0.7067 0.0086
-9.750 -0.5026 0.01805 0.01096 -0.1092 0.7046 0.0090
-9.500 -0.4839 0.01752 0.01037 -0.1082 0.7023 0.0094
-9.250 -0.4640 0.01703 0.00985 -0.1074 0.7000 0.0101
-9.000 -0.4431 0.01660 0.00935 -0.1067 0.6978 0.0107
-8.750 -0.4212 0.01621 0.00889 -0.1061 0.6958 0.0116
-8.500 -0.3993 0.01579 0.00843 -0.1055 0.6940 0.0124
-8.250 -0.3765 0.01544 0.00802 -0.1050 0.6923 0.0135
-8.000 -0.3530 0.01509 0.00764 -0.1046 0.6908 0.0150
-7.750 -0.3292 0.01474 0.00728 -0.1043 0.6891 0.0169
-7.500 -0.3051 0.01441 0.00693 -0.1040 0.6874 0.0189
-7.250 -0.2804 0.01411 0.00661 -0.1037 0.6855 0.0216
-7.000 -0.2557 0.01380 0.00630 -0.1035 0.6836 0.0247
-6.750 -0.2307 0.01350 0.00600 -0.1033 0.6817 0.0284
-6.500 -0.2054 0.01323 0.00571 -0.1032 0.6801 0.0323
-6.250 -0.1797 0.01297 0.00544 -0.1031 0.6786 0.0371
-6.000 -0.1538 0.01273 0.00519 -0.1030 0.6771 0.0433
-5.750 -0.1278 0.01248 0.00495 -0.1030 0.6756 0.0517
-5.500 -0.1017 0.01222 0.00473 -0.1030 0.6741 0.0619
-5.250 -0.0753 0.01196 0.00452 -0.1030 0.6724 0.0739
-5.000 -0.0488 0.01172 0.00433 -0.1031 0.6707 0.0884
-4.750 -0.0219 0.01149 0.00415 -0.1032 0.6691 0.1053
-4.500 0.0049 0.01124 0.00398 -0.1033 0.6675 0.1257
-4.250 0.0319 0.01101 0.00382 -0.1035 0.6660 0.1501
-4.000 0.0589 0.01075 0.00366 -0.1037 0.6643 0.1809
-3.750 0.0861 0.01049 0.00351 -0.1039 0.6627 0.2158
-3.500 0.1136 0.01025 0.00337 -0.1042 0.6611 0.2521
-3.250 0.1412 0.01000 0.00325 -0.1046 0.6597 0.2968
-3.000 0.1690 0.00974 0.00314 -0.1050 0.6584 0.3463
-2.750 0.1968 0.00946 0.00304 -0.1054 0.6568 0.3988
-2.500 0.2247 0.00915 0.00295 -0.1058 0.6551 0.4599
-2.250 0.2528 0.00888 0.00290 -0.1062 0.6533 0.5240
-2.000 0.2811 0.00871 0.00291 -0.1066 0.6517 0.5803
-1.750 0.3099 0.00867 0.00295 -0.1068 0.6499 0.6173
-1.500 0.3388 0.00867 0.00298 -0.1071 0.6482 0.6401
-1.250 0.3679 0.00870 0.00301 -0.1075 0.6465 0.6570
-1.000 0.3972 0.00874 0.00302 -0.1078 0.6449 0.6704
-0.750 0.4264 0.00880 0.00306 -0.1082 0.6433 0.6813
-0.500 0.4554 0.00884 0.00310 -0.1085 0.6416 0.6899
-0.250 0.4841 0.00888 0.00316 -0.1088 0.6397 0.6981
0.000 0.5130 0.00892 0.00320 -0.1091 0.6375 0.7052
0.250 0.5416 0.00896 0.00326 -0.1093 0.6352 0.7120
0.500 0.5706 0.00900 0.00328 -0.1097 0.6328 0.7190
0.750 0.5991 0.00904 0.00331 -0.1099 0.6304 0.7243
1.000 0.6278 0.00909 0.00334 -0.1102 0.6280 0.7298
1.250 0.6566 0.00915 0.00339 -0.1105 0.6254 0.7356
1.500 0.6846 0.00918 0.00346 -0.1107 0.6225 0.7402
1.750 0.7126 0.00922 0.00353 -0.1108 0.6195 0.7443
2.000 0.7409 0.00925 0.00358 -0.1111 0.6165 0.7482
2.250 0.7695 0.00929 0.00360 -0.1114 0.6136 0.7517
2.500 0.7981 0.00935 0.00362 -0.1117 0.6106 0.7549
2.750 0.8254 0.00937 0.00371 -0.1118 0.6068 0.7575
3.000 0.8529 0.00940 0.00378 -0.1119 0.6027 0.7602
3.250 0.8805 0.00944 0.00383 -0.1120 0.5987 0.7631
3.500 0.9082 0.00950 0.00388 -0.1121 0.5950 0.7661
3.750 0.9356 0.00954 0.00397 -0.1122 0.5899 0.7690
4.250 0.9892 0.00965 0.00410 -0.1122 0.5795 0.7742
4.500 1.0156 0.00971 0.00421 -0.1121 0.5731 0.7767
4.750 1.0412 0.00978 0.00429 -0.1119 0.5662 0.7792
5.000 1.0671 0.00986 0.00441 -0.1117 0.5587 0.7821
5.250 1.0916 0.00997 0.00450 -0.1113 0.5498 0.7852
5.500 1.1163 0.01009 0.00463 -0.1110 0.5390 0.7883
5.750 1.1390 0.01024 0.00478 -0.1102 0.5272 0.7908
6.000 1.1601 0.01043 0.00496 -0.1091 0.5133 0.7935
6.250 1.1794 0.01068 0.00518 -0.1078 0.4975 0.7966
6.500 1.1967 0.01098 0.00543 -0.1061 0.4802 0.8000
6.750 1.2103 0.01136 0.00575 -0.1037 0.4610 0.8039
7.000 1.2188 0.01176 0.00609 -0.1004 0.4430 0.8077
7.250 1.2262 0.01226 0.00655 -0.0969 0.4249 0.8115
7.500 1.2331 0.01285 0.00708 -0.0936 0.4061 0.8158
7.750 1.2391 0.01352 0.00770 -0.0903 0.3876 0.8204
8.000 1.2441 0.01426 0.00840 -0.0870 0.3704 0.8247
8.250 1.2491 0.01507 0.00920 -0.0839 0.3545 0.8297
8.500 1.2538 0.01600 0.01010 -0.0810 0.3387 0.8355
8.750 1.2579 0.01704 0.01111 -0.0782 0.3226 0.8409
9.000 1.2627 0.01811 0.01217 -0.0757 0.3080 0.8466
9.250 1.2670 0.01931 0.01334 -0.0732 0.2926 0.8530
9.500 1.2719 0.02052 0.01455 -0.0710 0.2786 0.8592
9.750 1.2771 0.02177 0.01579 -0.0689 0.2653 0.8665
10.000 1.2813 0.02311 0.01711 -0.0668 0.2510 0.8745
10.250 1.2865 0.02440 0.01839 -0.0648 0.2382 0.8842
10.500 1.2919 0.02566 0.01967 -0.0628 0.2256 0.8955
10.750 1.2961 0.02697 0.02100 -0.0608 0.2130 0.9109
11.000 1.3016 0.02834 0.02238 -0.0591 0.2005 0.9380
11.750 1.3254 0.03276 0.02674 -0.0562 0.1662 1.0000
12.000 1.3334 0.03429 0.02824 -0.0552 0.1557 1.0000
12.250 1.3405 0.03591 0.02984 -0.0543 0.1457 1.0000
12.500 1.3474 0.03760 0.03149 -0.0534 0.1356 1.0000
12.750 1.3563 0.03916 0.03305 -0.0526 0.1269 1.0000
13.000 1.3639 0.04085 0.03473 -0.0519 0.1192 1.0000
13.250 1.3711 0.04261 0.03647 -0.0512 0.1104 1.0000
13.500 1.3783 0.04441 0.03827 -0.0505 0.1022 1.0000
13.750 1.3851 0.04628 0.04013 -0.0499 0.0951 1.0000
14.000 1.3917 0.04820 0.04205 -0.0494 0.0874 1.0000
14.250 1.3986 0.05012 0.04398 -0.0489 0.0815 1.0000
14.500 1.4045 0.05220 0.04606 -0.0484 0.0751 1.0000
14.750 1.4112 0.05423 0.04811 -0.0481 0.0701 1.0000
15.000 1.4169 0.05639 0.05029 -0.0478 0.0648 1.0000
15.250 1.4228 0.05859 0.05252 -0.0475 0.0605 1.0000
15.500 1.4284 0.06083 0.05478 -0.0474 0.0562 1.0000
15.750 1.4327 0.06328 0.05727 -0.0472 0.0521 1.0000
16.000 1.4378 0.06568 0.05970 -0.0472 0.0483 1.0000
16.250 1.4410 0.06835 0.06241 -0.0472 0.0449 1.0000
16.500 1.4455 0.07089 0.06500 -0.0473 0.0417 1.0000
16.750 1.4473 0.07382 0.06796 -0.0475 0.0388 1.0000
17.000 1.4514 0.07650 0.07071 -0.0478 0.0363 1.0000
17.250 1.4532 0.07954 0.07379 -0.0481 0.0337 1.0000
17.500 1.4546 0.08266 0.07698 -0.0486 0.0318 1.0000
17.750 1.4573 0.08567 0.08006 -0.0491 0.0298 1.0000
18.000 1.4567 0.08914 0.08358 -0.0498 0.0278 1.0000
18.250 1.4574 0.09251 0.08702 -0.0505 0.0262 1.0000
18.500 1.4580 0.09593 0.09052 -0.0513 0.0245 1.0000
18.750 1.4561 0.09975 0.09440 -0.0524 0.0230 1.0000
19.000 1.4556 0.10343 0.09816 -0.0535 0.0218 1.0000
19.250 1.4545 0.10719 0.10200 -0.0547 0.0202 1.0000
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