EPPLER 655 AIRFOIL (e655-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 655 AIRFOIL (e655-il) Reynolds number: 1,000,000 Max Cl/Cd: 150.47 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e655-il-1000000.txt Download as CSV file: xf-e655-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.000 -0.3927 0.13000 0.12803 -0.0738 0.9389 0.0071
-16.750 -0.3456 0.12578 0.12372 -0.0853 0.9191 0.0073
-16.500 -0.5358 0.09190 0.08949 -0.0916 0.9386 0.0066
-16.250 -0.5625 0.07785 0.07517 -0.1049 0.9288 0.0065
-16.000 -0.5471 0.06990 0.06687 -0.1169 0.8858 0.0066
-15.750 -0.5814 0.06135 0.05793 -0.1216 0.8466 0.0065
-15.500 -0.6026 0.05511 0.05143 -0.1249 0.8257 0.0065
-15.250 -0.6118 0.05073 0.04687 -0.1272 0.8106 0.0064
-15.000 -0.6178 0.04694 0.04293 -0.1292 0.7989 0.0065
-14.750 -0.6268 0.04315 0.03898 -0.1308 0.7894 0.0065
-14.500 -0.6385 0.03943 0.03509 -0.1319 0.7808 0.0064
-14.250 -0.6450 0.03654 0.03204 -0.1323 0.7736 0.0065
-14.000 -0.6439 0.03447 0.02987 -0.1324 0.7673 0.0065
-13.750 -0.6468 0.03225 0.02750 -0.1320 0.7613 0.0066
-13.500 -0.6488 0.03019 0.02531 -0.1313 0.7561 0.0066
-13.250 -0.6467 0.02852 0.02354 -0.1305 0.7513 0.0066
-13.000 -0.6433 0.02705 0.02195 -0.1295 0.7466 0.0066
-12.750 -0.6393 0.02571 0.02048 -0.1282 0.7419 0.0066
-12.500 -0.6352 0.02433 0.01900 -0.1269 0.7387 0.0067
-12.250 -0.6277 0.02323 0.01781 -0.1255 0.7353 0.0068
-12.000 -0.6205 0.02217 0.01667 -0.1240 0.7319 0.0068
-11.750 -0.6119 0.02123 0.01562 -0.1224 0.7286 0.0069
-11.500 -0.6013 0.02047 0.01476 -0.1209 0.7251 0.0069
-11.250 -0.5930 0.01955 0.01378 -0.1191 0.7229 0.0069
-11.000 -0.5886 0.01852 0.01266 -0.1165 0.7204 0.0071
-10.750 -0.5866 0.01766 0.01172 -0.1132 0.7177 0.0073
-10.500 -0.5741 0.01702 0.01100 -0.1114 0.7151 0.0074
-10.250 -0.5582 0.01642 0.01034 -0.1101 0.7125 0.0076
-10.000 -0.5395 0.01595 0.00980 -0.1091 0.7098 0.0080
-9.750 -0.5194 0.01550 0.00930 -0.1082 0.7076 0.0082
-9.500 -0.4982 0.01505 0.00881 -0.1075 0.7060 0.0086
-9.250 -0.4757 0.01467 0.00838 -0.1070 0.7043 0.0091
-9.000 -0.4559 0.01405 0.00772 -0.1061 0.7024 0.0098
-8.750 -0.4326 0.01370 0.00734 -0.1057 0.7006 0.0107
-8.500 -0.4085 0.01338 0.00698 -0.1053 0.6987 0.0115
-8.250 -0.3855 0.01294 0.00651 -0.1048 0.6967 0.0128
-8.000 -0.3603 0.01271 0.00624 -0.1046 0.6946 0.0143
-7.750 -0.3360 0.01237 0.00588 -0.1043 0.6923 0.0165
-7.500 -0.3107 0.01207 0.00557 -0.1042 0.6909 0.0187
-7.250 -0.2847 0.01182 0.00531 -0.1041 0.6896 0.0211
-7.000 -0.2590 0.01152 0.00503 -0.1040 0.6882 0.0242
-6.750 -0.2328 0.01126 0.00478 -0.1040 0.6866 0.0277
-6.500 -0.2063 0.01102 0.00454 -0.1040 0.6849 0.0318
-6.250 -0.1796 0.01079 0.00432 -0.1040 0.6832 0.0368
-6.000 -0.1528 0.01055 0.00411 -0.1041 0.6816 0.0438
-5.750 -0.1261 0.01031 0.00391 -0.1042 0.6801 0.0537
-5.500 -0.0991 0.01008 0.00372 -0.1043 0.6785 0.0656
-5.250 -0.0719 0.00988 0.00357 -0.1045 0.6766 0.0816
-5.000 -0.0446 0.00965 0.00342 -0.1047 0.6748 0.1026
-4.750 -0.0173 0.00939 0.00326 -0.1049 0.6737 0.1262
-4.500 0.0104 0.00915 0.00312 -0.1052 0.6723 0.1519
-4.250 0.0381 0.00890 0.00298 -0.1055 0.6709 0.1829
-4.000 0.0660 0.00865 0.00286 -0.1058 0.6695 0.2178
-3.750 0.0940 0.00839 0.00274 -0.1062 0.6679 0.2588
-3.500 0.1220 0.00810 0.00261 -0.1066 0.6663 0.3097
-3.250 0.1503 0.00781 0.00250 -0.1071 0.6648 0.3657
-3.000 0.1788 0.00753 0.00240 -0.1076 0.6633 0.4243
-2.750 0.2075 0.00724 0.00231 -0.1082 0.6616 0.4946
-2.500 0.2366 0.00704 0.00230 -0.1088 0.6596 0.5619
-2.250 0.2659 0.00694 0.00232 -0.1092 0.6581 0.6098
-2.000 0.2954 0.00690 0.00234 -0.1097 0.6569 0.6379
-1.750 0.3249 0.00689 0.00236 -0.1101 0.6554 0.6556
-1.500 0.3546 0.00691 0.00237 -0.1105 0.6538 0.6692
-1.250 0.3840 0.00691 0.00240 -0.1109 0.6521 0.6796
-1.000 0.4137 0.00694 0.00240 -0.1113 0.6503 0.6883
-0.750 0.4431 0.00696 0.00242 -0.1117 0.6485 0.6964
-0.500 0.4729 0.00701 0.00243 -0.1122 0.6467 0.7035
-0.250 0.5021 0.00707 0.00248 -0.1126 0.6443 0.7097
0.000 0.5316 0.00714 0.00254 -0.1130 0.6420 0.7157
0.250 0.5609 0.00715 0.00255 -0.1134 0.6401 0.7208
0.500 0.5898 0.00714 0.00258 -0.1137 0.6379 0.7257
0.750 0.6190 0.00717 0.00261 -0.1140 0.6357 0.7307
1.000 0.6483 0.00720 0.00263 -0.1145 0.6334 0.7356
1.250 0.6774 0.00722 0.00264 -0.1148 0.6311 0.7400
1.500 0.7063 0.00727 0.00268 -0.1151 0.6284 0.7441
1.750 0.7353 0.00734 0.00275 -0.1155 0.6257 0.7483
2.000 0.7641 0.00735 0.00279 -0.1158 0.6233 0.7525
2.250 0.7928 0.00735 0.00281 -0.1161 0.6204 0.7563
2.500 0.8213 0.00735 0.00283 -0.1164 0.6174 0.7598
2.750 0.8498 0.00738 0.00286 -0.1167 0.6143 0.7628
3.000 0.8785 0.00746 0.00291 -0.1170 0.6108 0.7658
3.250 0.9068 0.00746 0.00296 -0.1173 0.6077 0.7687
3.500 0.9354 0.00747 0.00299 -0.1176 0.6039 0.7712
3.750 0.9634 0.00747 0.00301 -0.1178 0.6000 0.7740
4.000 0.9911 0.00753 0.00306 -0.1179 0.5957 0.7767
4.250 1.0190 0.00754 0.00312 -0.1181 0.5915 0.7793
4.500 1.0467 0.00757 0.00318 -0.1183 0.5862 0.7819
4.750 1.0737 0.00764 0.00323 -0.1183 0.5807 0.7846
5.000 1.1015 0.00768 0.00331 -0.1185 0.5748 0.7873
5.250 1.1282 0.00774 0.00337 -0.1185 0.5677 0.7898
5.500 1.1546 0.00780 0.00346 -0.1184 0.5603 0.7925
5.750 1.1798 0.00790 0.00356 -0.1181 0.5509 0.7951
6.000 1.2053 0.00801 0.00368 -0.1179 0.5401 0.7980
6.250 1.2293 0.00817 0.00382 -0.1174 0.5276 0.8011
6.500 1.2517 0.00839 0.00399 -0.1166 0.5117 0.8041
6.750 1.2721 0.00865 0.00421 -0.1155 0.4935 0.8071
7.000 1.2900 0.00897 0.00447 -0.1139 0.4742 0.8104
7.250 1.3062 0.00935 0.00478 -0.1120 0.4528 0.8137
7.500 1.3192 0.00978 0.00513 -0.1095 0.4306 0.8176
7.750 1.3270 0.01023 0.00550 -0.1060 0.4109 0.8216
8.000 1.3349 0.01071 0.00594 -0.1026 0.3920 0.8262
8.250 1.3426 0.01124 0.00642 -0.0993 0.3735 0.8308
8.500 1.3498 0.01184 0.00697 -0.0961 0.3557 0.8357
8.750 1.3551 0.01254 0.00761 -0.0927 0.3375 0.8407
9.000 1.3597 0.01330 0.00835 -0.0894 0.3209 0.8462
9.250 1.3642 0.01417 0.00918 -0.0863 0.3047 0.8524
9.500 1.3675 0.01517 0.01014 -0.0833 0.2884 0.8589
9.750 1.3723 0.01618 0.01114 -0.0806 0.2741 0.8662
10.000 1.3769 0.01730 0.01223 -0.0780 0.2596 0.8737
10.250 1.3807 0.01849 0.01341 -0.0755 0.2451 0.8825
10.500 1.3845 0.01973 0.01463 -0.0731 0.2311 0.8926
10.750 1.3882 0.02098 0.01588 -0.0707 0.2182 0.9056
11.000 1.3901 0.02223 0.01716 -0.0681 0.2057 0.9279
11.250 1.3981 0.02346 0.01843 -0.0668 0.1936 1.0000
11.500 1.4053 0.02485 0.01978 -0.0654 0.1813 1.0000
11.750 1.4127 0.02623 0.02112 -0.0641 0.1700 1.0000
12.000 1.4190 0.02772 0.02257 -0.0627 0.1590 1.0000
12.250 1.4245 0.02929 0.02409 -0.0613 0.1480 1.0000
12.500 1.4319 0.03076 0.02552 -0.0601 0.1380 1.0000
12.750 1.4392 0.03229 0.02703 -0.0590 0.1286 1.0000
13.000 1.4457 0.03389 0.02860 -0.0579 0.1194 1.0000
13.250 1.4515 0.03559 0.03027 -0.0569 0.1104 1.0000
13.500 1.4604 0.03709 0.03177 -0.0560 0.1034 1.0000
13.750 1.4658 0.03890 0.03355 -0.0551 0.0950 1.0000
14.000 1.4708 0.04079 0.03539 -0.0542 0.0860 1.0000
14.250 1.4788 0.04245 0.03707 -0.0535 0.0801 1.0000
14.500 1.4833 0.04447 0.03906 -0.0527 0.0732 1.0000
14.750 1.4905 0.04629 0.04087 -0.0521 0.0671 1.0000
15.000 1.4956 0.04835 0.04293 -0.0515 0.0615 1.0000
15.250 1.4995 0.05053 0.04508 -0.0509 0.0548 1.0000
15.500 1.5065 0.05249 0.04707 -0.0505 0.0515 1.0000
15.750 1.5097 0.05486 0.04941 -0.0501 0.0460 1.0000
16.000 1.5153 0.05704 0.05162 -0.0498 0.0422 1.0000
16.250 1.5198 0.05936 0.05396 -0.0496 0.0393 1.0000
16.500 1.5253 0.06162 0.05626 -0.0494 0.0366 1.0000
16.750 1.5277 0.06426 0.05891 -0.0493 0.0332 1.0000
17.000 1.5326 0.06669 0.06139 -0.0493 0.0312 1.0000
17.250 1.5360 0.06932 0.06405 -0.0493 0.0288 1.0000
17.500 1.5377 0.07220 0.06697 -0.0495 0.0266 1.0000
17.750 1.5418 0.07483 0.06965 -0.0497 0.0250 1.0000
18.000 1.5423 0.07799 0.07284 -0.0500 0.0233 1.0000
18.250 1.5448 0.08091 0.07582 -0.0504 0.0219 1.0000
18.500 1.5466 0.08399 0.07896 -0.0509 0.0207 1.0000
18.750 1.5463 0.08738 0.08240 -0.0516 0.0194 1.0000
19.000 1.5464 0.09074 0.08583 -0.0523 0.0183 1.0000
19.250 1.5470 0.09411 0.08927 -0.0531 0.0173 1.0000
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Polar data table (+)
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