GOE 15 AIRFOIL (goe15-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
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Airfoil: GOE 15 AIRFOIL (goe15-il) Reynolds number: 1,000,000 Max Cl/Cd: 128.66 at α=9.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe15-il-1000000.txt Download as CSV file: xf-goe15-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 15 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
------ -------- --------- --------- -------- -------- --------
-9.500 0.0313 0.09036 0.08836 -0.0916 0.9026 0.0185
-9.250 0.0525 0.08730 0.08513 -0.0960 0.8691 0.0194
-9.000 0.0577 0.08504 0.08268 -0.0973 0.8271 0.0199
-8.750 0.0598 0.08330 0.08075 -0.0972 0.7862 0.0199
-8.500 0.0614 0.08143 0.07877 -0.0974 0.7625 0.0199
-8.250 0.0694 0.07863 0.07590 -0.0969 0.7492 0.0201
-8.000 0.0767 0.07668 0.07392 -0.0969 0.7393 0.0202
-7.750 0.0833 0.07493 0.07213 -0.0967 0.7306 0.0203
-7.500 0.0888 0.07324 0.07043 -0.0965 0.7235 0.0205
-7.250 0.0919 0.07172 0.06889 -0.0960 0.7165 0.0207
-7.000 0.0995 0.06997 0.06714 -0.0965 0.7107 0.0213
-6.750 0.1091 0.06794 0.06509 -0.0975 0.7052 0.0219
-6.500 0.1197 0.06570 0.06282 -0.0991 0.6998 0.0227
-6.250 0.1331 0.06339 0.06048 -0.1022 0.6949 0.0230
-6.000 0.1488 0.06095 0.05800 -0.1053 0.6901 0.0230
-5.750 0.1601 0.05810 0.05514 -0.1051 0.6849 0.0232
-5.500 0.1742 0.05609 0.05308 -0.1054 0.6790 0.0233
-5.250 0.1910 0.05422 0.05121 -0.1063 0.6740 0.0236
-5.000 0.2092 0.05234 0.04930 -0.1074 0.6678 0.0239
-4.750 0.2280 0.05046 0.04735 -0.1085 0.6618 0.0243
-4.500 0.2486 0.04844 0.04531 -0.1099 0.6562 0.0250
-4.250 0.2738 0.04626 0.04306 -0.1120 0.6494 0.0261
-4.000 0.3041 0.04406 0.04070 -0.1150 0.6425 0.0263
-3.750 0.3238 0.04137 0.03796 -0.1157 0.6345 0.0264
-3.500 0.3413 0.03946 0.03600 -0.1156 0.6248 0.0266
-3.250 0.3622 0.03786 0.03435 -0.1158 0.6126 0.0268
-3.000 0.3841 0.03640 0.03279 -0.1161 0.5974 0.0271
-2.750 0.4066 0.03501 0.03128 -0.1163 0.5787 0.0275
-2.500 0.4292 0.03364 0.02976 -0.1163 0.5556 0.0282
-2.250 0.4530 0.03229 0.02821 -0.1163 0.5274 0.0293
-2.000 0.4866 0.03096 0.02656 -0.1166 0.5020 0.0298
-1.750 0.5057 0.02898 0.02443 -0.1161 0.4813 0.0299
-1.500 0.5252 0.02771 0.02306 -0.1156 0.4656 0.0301
-1.250 0.5473 0.02667 0.02192 -0.1152 0.4543 0.0304
-1.000 0.5709 0.02571 0.02087 -0.1149 0.4458 0.0309
-0.750 0.5951 0.02475 0.01980 -0.1145 0.4384 0.0314
-0.500 0.6208 0.02373 0.01869 -0.1141 0.4329 0.0326
-0.250 0.6531 0.02289 0.01759 -0.1132 0.4275 0.0335
0.000 0.6746 0.02124 0.01583 -0.1126 0.4217 0.0338
0.250 0.6980 0.02032 0.01489 -0.1123 0.4183 0.0340
0.500 0.7221 0.01960 0.01411 -0.1119 0.4145 0.0344
0.750 0.7467 0.01897 0.01340 -0.1113 0.4105 0.0352
1.000 0.7754 0.01860 0.01283 -0.1102 0.4061 0.0374
1.250 0.8016 0.01788 0.01198 -0.1094 0.4029 0.0375
1.500 0.8249 0.01656 0.01061 -0.1089 0.4002 0.0380
1.750 0.8492 0.01604 0.01006 -0.1085 0.3970 0.0384
2.000 0.8738 0.01560 0.00957 -0.1079 0.3935 0.0391
2.250 0.8982 0.01525 0.00911 -0.1071 0.3886 0.0407
2.500 0.9264 0.01508 0.00874 -0.1060 0.3854 0.0420
2.750 0.9503 0.01405 0.00769 -0.1055 0.3826 0.0427
3.000 0.9751 0.01373 0.00735 -0.1050 0.3793 0.0432
3.250 0.9998 0.01351 0.00709 -0.1044 0.3758 0.0446
3.500 1.0255 0.01365 0.00705 -0.1033 0.3710 0.0471
3.750 1.0496 0.01282 0.00621 -0.1028 0.3680 0.0480
4.000 1.0748 0.01259 0.00599 -0.1023 0.3652 0.0488
4.250 1.0998 0.01243 0.00581 -0.1018 0.3623 0.0504
4.500 1.1246 0.01223 0.00552 -0.1010 0.3592 0.0538
4.750 1.1482 0.01210 0.00540 -0.1002 0.3559 0.0549
5.000 1.1717 0.01207 0.00534 -0.0994 0.3525 0.0570
5.250 1.1969 0.01191 0.00518 -0.0989 0.3502 0.0611
5.500 1.2212 0.01180 0.00511 -0.0983 0.3470 0.0630
5.750 1.2450 0.01179 0.00508 -0.0975 0.3434 0.0690
6.000 1.2675 0.01177 0.00508 -0.0966 0.3397 0.0723
6.250 1.2893 0.01176 0.00506 -0.0954 0.3361 0.0726
6.500 1.3114 0.01147 0.00474 -0.0940 0.3337 0.0555
6.750 1.3346 0.01150 0.00481 -0.0932 0.3304 0.0570
7.000 1.3568 0.01157 0.00489 -0.0922 0.3267 0.0582
7.250 1.3778 0.01170 0.00500 -0.0910 0.3226 0.0590
7.500 1.3986 0.01180 0.00512 -0.0898 0.3189 0.0599
7.750 1.4197 0.01183 0.00519 -0.0885 0.3152 0.0616
8.000 1.4389 0.01196 0.00532 -0.0870 0.3093 0.0643
8.250 1.4571 0.01214 0.00549 -0.0853 0.3028 0.0662
8.500 1.4771 0.01228 0.00565 -0.0839 0.2969 0.0683
8.750 1.4945 0.01252 0.00587 -0.0821 0.2903 0.0726
9.000 1.5136 0.01272 0.00609 -0.0807 0.2836 0.0789
9.250 1.5761 0.01225 0.00684 -0.0894 0.2697 1.0000
9.500 1.5915 0.01261 0.00715 -0.0874 0.2594 1.0000
9.750 1.6068 0.01299 0.00749 -0.0854 0.2475 1.0000
10.000 1.6207 0.01347 0.00790 -0.0832 0.2346 1.0000
10.250 1.6339 0.01399 0.00837 -0.0811 0.2223 1.0000
10.500 1.6458 0.01459 0.00891 -0.0788 0.2094 1.0000
10.750 1.6569 0.01527 0.00951 -0.0765 0.1969 1.0000
11.000 1.6679 0.01597 0.01017 -0.0742 0.1856 1.0000
11.250 1.6789 0.01670 0.01086 -0.0721 0.1752 1.0000
11.500 1.6896 0.01747 0.01160 -0.0701 0.1668 1.0000
11.750 1.7024 0.01815 0.01229 -0.0684 0.1611 1.0000
12.000 1.7121 0.01905 0.01317 -0.0664 0.1536 1.0000
12.250 1.7239 0.01984 0.01398 -0.0648 0.1473 1.0000
12.500 1.7319 0.02092 0.01502 -0.0629 0.1391 1.0000
12.750 1.7376 0.02218 0.01624 -0.0609 0.1284 1.0000
13.000 1.7396 0.02377 0.01777 -0.0587 0.1145 1.0000
13.250 1.7318 0.02618 0.02005 -0.0560 0.0934 1.0000
13.500 1.7187 0.02923 0.02300 -0.0534 0.0737 1.0000
13.750 1.7013 0.03290 0.02658 -0.0511 0.0553 1.0000
14.000 1.6787 0.03730 0.03090 -0.0490 0.0370 1.0000
14.250 1.6585 0.04171 0.03529 -0.0475 0.0223 1.0000
14.500 1.6479 0.04535 0.03898 -0.0466 0.0179 1.0000
14.750 1.6427 0.04854 0.04224 -0.0460 0.0166 1.0000
15.000 1.6382 0.05176 0.04554 -0.0455 0.0157 1.0000
15.250 1.6349 0.05494 0.04881 -0.0453 0.0151 1.0000
15.500 1.6295 0.05842 0.05239 -0.0451 0.0147 1.0000
15.750 1.6231 0.06216 0.05622 -0.0452 0.0143 1.0000
16.000 1.6155 0.06615 0.06030 -0.0453 0.0140 1.0000
16.250 1.6064 0.07036 0.06462 -0.0456 0.0136 1.0000
16.500 1.5951 0.07498 0.06933 -0.0461 0.0132 1.0000
16.750 1.5827 0.07983 0.07429 -0.0467 0.0129 1.0000
17.000 1.5750 0.08401 0.07857 -0.0472 0.0127 1.0000
17.250 1.5663 0.08836 0.08301 -0.0479 0.0126 1.0000
17.500 1.5571 0.09279 0.08753 -0.0486 0.0125 1.0000
17.750 1.5491 0.09709 0.09192 -0.0493 0.0122 1.0000
18.000 1.5388 0.10174 0.09666 -0.0502 0.0121 1.0000
18.250 1.5297 0.10621 0.10122 -0.0511 0.0118 1.0000
18.500 1.5199 0.11085 0.10594 -0.0522 0.0116 1.0000
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