EPPLER 655 AIRFOIL (e655-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 655 AIRFOIL (e655-il) Reynolds number: 500,000 Max Cl/Cd: 116.85 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e655-il-500000.txt Download as CSV file: xf-e655-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.750 -0.3882 0.07985 0.07672 -0.1121 0.8785 0.0115
-14.500 -0.4169 0.07035 0.06694 -0.1184 0.8564 0.0113
-14.250 -0.4438 0.06222 0.05854 -0.1237 0.8406 0.0112
-14.000 -0.4639 0.05602 0.05211 -0.1275 0.8283 0.0111
-13.750 -0.4844 0.05046 0.04632 -0.1306 0.8184 0.0111
-13.500 -0.5027 0.04587 0.04147 -0.1326 0.8099 0.0111
-13.250 -0.5176 0.04203 0.03742 -0.1335 0.8025 0.0110
-13.000 -0.5260 0.03916 0.03435 -0.1336 0.7960 0.0110
-12.750 -0.5326 0.03657 0.03156 -0.1333 0.7903 0.0109
-12.500 -0.5408 0.03394 0.02871 -0.1324 0.7846 0.0110
-12.250 -0.5434 0.03192 0.02648 -0.1312 0.7795 0.0112
-12.000 -0.5416 0.03020 0.02456 -0.1300 0.7750 0.0111
-11.750 -0.5392 0.02856 0.02274 -0.1285 0.7711 0.0113
-11.500 -0.5328 0.02725 0.02129 -0.1272 0.7671 0.0114
-11.250 -0.5250 0.02592 0.01982 -0.1257 0.7636 0.0114
-11.000 -0.5162 0.02491 0.01861 -0.1242 0.7602 0.0117
-10.750 -0.5093 0.02330 0.01691 -0.1224 0.7572 0.0120
-10.500 -0.4987 0.02232 0.01589 -0.1209 0.7542 0.0122
-10.250 -0.4879 0.02148 0.01499 -0.1192 0.7511 0.0125
-10.000 -0.4771 0.02083 0.01429 -0.1172 0.7481 0.0130
-9.750 -0.4652 0.02020 0.01355 -0.1153 0.7453 0.0134
-9.500 -0.4491 0.01958 0.01281 -0.1140 0.7426 0.0140
-9.250 -0.4336 0.01882 0.01197 -0.1127 0.7404 0.0147
-9.000 -0.4178 0.01809 0.01123 -0.1114 0.7381 0.0154
-8.750 -0.3979 0.01761 0.01072 -0.1106 0.7358 0.0166
-8.500 -0.3771 0.01714 0.01016 -0.1098 0.7336 0.0176
-8.250 -0.3594 0.01642 0.00943 -0.1087 0.7314 0.0191
-8.000 -0.3365 0.01606 0.00900 -0.1082 0.7292 0.0211
-7.750 -0.3157 0.01553 0.00845 -0.1075 0.7271 0.0235
-7.500 -0.2929 0.01515 0.00802 -0.1070 0.7249 0.0266
-7.250 -0.2684 0.01488 0.00774 -0.1068 0.7232 0.0301
-7.000 -0.2454 0.01445 0.00734 -0.1063 0.7214 0.0344
-6.750 -0.2215 0.01407 0.00697 -0.1060 0.7195 0.0395
-6.500 -0.1973 0.01370 0.00662 -0.1057 0.7175 0.0455
-6.250 -0.1725 0.01336 0.00628 -0.1055 0.7155 0.0533
-6.000 -0.1474 0.01302 0.00598 -0.1053 0.7136 0.0637
-5.750 -0.1218 0.01272 0.00570 -0.1053 0.7118 0.0781
-5.500 -0.0963 0.01241 0.00546 -0.1052 0.7101 0.0978
-5.250 -0.0703 0.01218 0.00530 -0.1053 0.7083 0.1218
-5.000 -0.0446 0.01186 0.00511 -0.1053 0.7069 0.1510
-4.750 -0.0189 0.01154 0.00494 -0.1054 0.7051 0.1855
-4.500 0.0072 0.01122 0.00477 -0.1055 0.7031 0.2263
-4.250 0.0335 0.01089 0.00461 -0.1056 0.7012 0.2740
-4.000 0.0601 0.01054 0.00447 -0.1059 0.6995 0.3320
-3.750 0.0870 0.01016 0.00432 -0.1062 0.6978 0.3993
-3.500 0.1142 0.00979 0.00419 -0.1066 0.6961 0.4719
-3.250 0.1418 0.00948 0.00413 -0.1069 0.6944 0.5511
-3.000 0.1701 0.00943 0.00423 -0.1071 0.6927 0.6098
-2.750 0.1987 0.00952 0.00436 -0.1073 0.6911 0.6425
-2.500 0.2271 0.00957 0.00443 -0.1075 0.6895 0.6648
-2.250 0.2556 0.00965 0.00451 -0.1076 0.6875 0.6810
-2.000 0.2842 0.00973 0.00459 -0.1078 0.6856 0.6937
-1.750 0.3133 0.00982 0.00465 -0.1081 0.6837 0.7050
-1.500 0.3420 0.00991 0.00473 -0.1082 0.6818 0.7142
-1.250 0.3712 0.00999 0.00478 -0.1085 0.6800 0.7229
-1.000 0.4002 0.01010 0.00486 -0.1087 0.6783 0.7304
-0.750 0.4300 0.01023 0.00493 -0.1092 0.6765 0.7381
-0.500 0.4580 0.01039 0.00510 -0.1092 0.6746 0.7437
-0.250 0.4858 0.01046 0.00519 -0.1093 0.6726 0.7502
0.000 0.5140 0.01052 0.00525 -0.1095 0.6703 0.7560
0.250 0.5415 0.01058 0.00534 -0.1094 0.6678 0.7609
0.500 0.5700 0.01064 0.00539 -0.1096 0.6654 0.7666
0.750 0.5998 0.01068 0.00538 -0.1101 0.6631 0.7721
1.000 0.6284 0.01072 0.00541 -0.1102 0.6609 0.7761
1.250 0.6571 0.01087 0.00554 -0.1105 0.6585 0.7805
1.500 0.6842 0.01090 0.00561 -0.1105 0.6560 0.7855
1.750 0.7121 0.01092 0.00566 -0.1106 0.6530 0.7898
2.000 0.7395 0.01092 0.00568 -0.1106 0.6502 0.7930
2.250 0.7681 0.01091 0.00568 -0.1109 0.6475 0.7962
2.500 0.7979 0.01092 0.00565 -0.1114 0.6449 0.7996
2.750 0.8273 0.01100 0.00570 -0.1119 0.6421 0.8031
3.000 0.8541 0.01098 0.00574 -0.1119 0.6386 0.8062
3.250 0.8808 0.01095 0.00576 -0.1118 0.6350 0.8088
3.500 0.9090 0.01091 0.00574 -0.1120 0.6317 0.8116
3.750 0.9382 0.01089 0.00569 -0.1124 0.6285 0.8145
4.000 0.9658 0.01092 0.00575 -0.1125 0.6249 0.8178
4.250 0.9925 0.01091 0.00579 -0.1126 0.6205 0.8210
4.500 1.0201 0.01085 0.00575 -0.1127 0.6162 0.8235
4.750 1.0480 0.01080 0.00571 -0.1128 0.6124 0.8262
5.000 1.0733 0.01082 0.00579 -0.1125 0.6077 0.8292
5.250 1.0990 0.01079 0.00581 -0.1123 0.6021 0.8323
5.500 1.1265 0.01076 0.00578 -0.1124 0.5971 0.8354
5.750 1.1521 0.01078 0.00585 -0.1122 0.5910 0.8387
6.000 1.1760 0.01075 0.00588 -0.1116 0.5843 0.8417
6.250 1.2004 0.01076 0.00593 -0.1111 0.5775 0.8449
6.500 1.2236 0.01079 0.00601 -0.1104 0.5690 0.8484
6.750 1.2472 0.01085 0.00610 -0.1098 0.5601 0.8521
7.000 1.2696 0.01093 0.00617 -0.1090 0.5498 0.8556
7.250 1.2888 0.01103 0.00632 -0.1076 0.5373 0.8593
7.500 1.3065 0.01119 0.00650 -0.1059 0.5231 0.8638
7.750 1.3224 0.01144 0.00672 -0.1039 0.5071 0.8687
8.000 1.3320 0.01171 0.00696 -0.1007 0.4901 0.8735
8.250 1.3373 0.01211 0.00732 -0.0968 0.4720 0.8793
8.500 1.3434 0.01263 0.00780 -0.0932 0.4528 0.8860
8.750 1.3450 0.01323 0.00837 -0.0890 0.4338 0.8932
9.000 1.3464 0.01399 0.00909 -0.0851 0.4152 0.9022
9.250 1.3443 0.01484 0.00992 -0.0807 0.3975 0.9126
9.500 1.3415 0.01583 0.01090 -0.0766 0.3801 0.9257
9.750 1.3391 0.01682 0.01190 -0.0726 0.3643 0.9482
10.000 1.3454 0.01812 0.01316 -0.0711 0.3457 1.0000
10.250 1.3514 0.01952 0.01451 -0.0695 0.3281 1.0000
10.500 1.3566 0.02099 0.01592 -0.0679 0.3115 1.0000
10.750 1.3609 0.02253 0.01740 -0.0662 0.2952 1.0000
11.000 1.3648 0.02411 0.01893 -0.0645 0.2793 1.0000
11.250 1.3685 0.02574 0.02050 -0.0629 0.2638 1.0000
11.500 1.3727 0.02737 0.02208 -0.0613 0.2493 1.0000
11.750 1.3763 0.02906 0.02372 -0.0598 0.2347 1.0000
12.000 1.3801 0.03081 0.02542 -0.0584 0.2212 1.0000
12.250 1.3852 0.03249 0.02706 -0.0571 0.2081 1.0000
12.500 1.3913 0.03414 0.02869 -0.0560 0.1958 1.0000
12.750 1.3970 0.03587 0.03039 -0.0550 0.1837 1.0000
13.000 1.4025 0.03766 0.03215 -0.0540 0.1726 1.0000
13.250 1.4067 0.03959 0.03405 -0.0530 0.1612 1.0000
13.500 1.4116 0.04151 0.03593 -0.0521 0.1502 1.0000
13.750 1.4183 0.04332 0.03774 -0.0513 0.1401 1.0000
14.000 1.4232 0.04532 0.03973 -0.0506 0.1304 1.0000
14.250 1.4266 0.04752 0.04189 -0.0499 0.1213 1.0000
14.500 1.4331 0.04947 0.04385 -0.0494 0.1125 1.0000
14.750 1.4381 0.05159 0.04598 -0.0488 0.1047 1.0000
15.000 1.4409 0.05399 0.04836 -0.0484 0.0970 1.0000
15.250 1.4471 0.05609 0.05049 -0.0480 0.0902 1.0000
15.500 1.4489 0.05871 0.05309 -0.0477 0.0836 1.0000
15.750 1.4540 0.06099 0.05541 -0.0475 0.0774 1.0000
16.000 1.4559 0.06371 0.05814 -0.0473 0.0719 1.0000
16.250 1.4594 0.06628 0.06074 -0.0472 0.0666 1.0000
16.500 1.4607 0.06919 0.06367 -0.0472 0.0618 1.0000
16.750 1.4633 0.07195 0.06648 -0.0473 0.0575 1.0000
17.000 1.4626 0.07521 0.06975 -0.0475 0.0534 1.0000
17.250 1.4655 0.07806 0.07267 -0.0478 0.0498 1.0000
17.500 1.4633 0.08163 0.07627 -0.0483 0.0466 1.0000
17.750 1.4650 0.08476 0.07947 -0.0488 0.0437 1.0000
18.000 1.4639 0.08828 0.08305 -0.0494 0.0408 1.0000
18.250 1.4593 0.09238 0.08719 -0.0502 0.0384 1.0000
18.500 1.4618 0.09552 0.09043 -0.0510 0.0361 1.0000
18.750 1.4588 0.09951 0.09446 -0.0521 0.0340 1.0000
19.000 1.4523 0.10407 0.09908 -0.0534 0.0323 1.0000
19.250 1.4547 0.10731 0.10243 -0.0544 0.0303 1.0000
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