GOE 123 AIRFOIL (goe123-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: GOE 123 AIRFOIL (goe123-il) Reynolds number: 200,000 Max Cl/Cd: 92.03 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe123-il-200000.txt Download as CSV file: xf-goe123-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 123 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3176 0.09649 0.09322 -0.0214 1.0000 0.0275
-7.250 -0.3355 0.09623 0.09304 -0.0169 1.0000 0.0277
-7.000 -0.3472 0.09529 0.09217 -0.0142 1.0000 0.0280
-6.750 -0.3510 0.09362 0.09054 -0.0136 0.9994 0.0284
-6.500 -0.3214 0.08943 0.08632 -0.0219 0.9950 0.0301
-6.250 -0.2617 0.08680 0.08355 -0.0444 0.9869 0.0313
-6.000 -0.2440 0.08062 0.07737 -0.0466 0.9843 0.0318
-5.750 -0.2297 0.07612 0.07289 -0.0462 0.9814 0.0324
-5.500 -0.2074 0.07249 0.06923 -0.0494 0.9764 0.0334
-5.250 -0.1751 0.06867 0.06535 -0.0556 0.9727 0.0350
-5.000 -0.1329 0.06470 0.06129 -0.0643 0.9699 0.0378
-4.750 -0.0688 0.06181 0.05811 -0.0793 0.9620 0.0402
-4.500 -0.0513 0.05663 0.05300 -0.0802 0.9588 0.0413
-4.250 -0.0169 0.05302 0.04933 -0.0846 0.9565 0.0431
-4.000 0.0172 0.05008 0.04631 -0.0890 0.9510 0.0459
-3.750 0.0824 0.04747 0.04329 -0.0997 0.9465 0.0512
-3.500 0.1076 0.04339 0.03928 -0.1020 0.9437 0.0527
-3.250 0.1434 0.04067 0.03649 -0.1056 0.9413 0.0555
-3.000 0.1920 0.04063 0.03603 -0.1097 0.9347 0.0627
-2.750 0.2209 0.03620 0.03156 -0.1126 0.9302 0.0643
-2.500 0.2503 0.03377 0.02916 -0.1145 0.9270 0.0676
-2.250 0.2931 0.03468 0.02957 -0.1161 0.9204 0.0764
-2.000 0.3176 0.03038 0.02535 -0.1178 0.9150 0.0784
-1.750 0.3482 0.02840 0.02336 -0.1192 0.9111 0.0819
-1.500 0.3814 0.02800 0.02255 -0.1192 0.9018 0.0915
-1.250 0.4085 0.02538 0.01998 -0.1198 0.8958 0.0945
-1.000 0.4380 0.02518 0.01944 -0.1191 0.8852 0.1058
-0.750 0.4622 0.02293 0.01729 -0.1191 0.8786 0.1103
-0.500 0.4907 0.02211 0.01626 -0.1189 0.8703 0.1214
-0.250 0.5176 0.02085 0.01495 -0.1186 0.8638 0.1274
0.000 0.5450 0.01988 0.01384 -0.1183 0.8551 0.1374
0.250 0.5821 0.01800 0.01121 -0.1169 0.8493 0.0767
0.500 0.6092 0.01619 0.00930 -0.1166 0.8403 0.0697
0.750 0.6375 0.01495 0.00777 -0.1158 0.8328 0.0653
1.000 0.6639 0.01444 0.00724 -0.1151 0.8235 0.0685
1.250 0.6904 0.01382 0.00656 -0.1143 0.8136 0.0688
1.500 0.7173 0.01323 0.00591 -0.1135 0.8049 0.0691
1.750 0.7436 0.01279 0.00548 -0.1128 0.7936 0.0709
2.000 0.7699 0.01244 0.00515 -0.1120 0.7815 0.0741
2.250 0.7964 0.01210 0.00483 -0.1114 0.7689 0.0811
2.500 0.8228 0.01185 0.00465 -0.1106 0.7541 0.1060
2.750 0.8484 0.01122 0.00452 -0.1100 0.7376 0.3655
3.000 0.8705 0.01013 0.00437 -0.1081 0.7201 1.0000
3.250 0.8964 0.01018 0.00429 -0.1073 0.6998 1.0000
3.500 0.9220 0.01027 0.00426 -0.1066 0.6767 1.0000
3.750 0.9473 0.01040 0.00427 -0.1058 0.6507 1.0000
4.000 0.9722 0.01058 0.00433 -0.1050 0.6213 1.0000
4.250 0.9967 0.01083 0.00441 -0.1041 0.5896 1.0000
4.500 1.0209 0.01116 0.00458 -0.1033 0.5587 1.0000
4.750 1.0448 0.01156 0.00481 -0.1025 0.5288 1.0000
5.000 1.0685 0.01200 0.00512 -0.1017 0.4999 1.0000
5.250 1.0922 0.01244 0.00546 -0.1009 0.4729 1.0000
5.500 1.1155 0.01290 0.00581 -0.1002 0.4458 1.0000
5.750 1.1383 0.01338 0.00616 -0.0993 0.4180 1.0000
6.000 1.1611 0.01386 0.00656 -0.0985 0.3929 1.0000
6.250 1.1841 0.01433 0.00698 -0.0978 0.3707 1.0000
6.500 1.2063 0.01485 0.00741 -0.0969 0.3478 1.0000
6.750 1.2287 0.01533 0.00787 -0.0962 0.3247 1.0000
7.000 1.2503 0.01587 0.00836 -0.0953 0.3017 1.0000
7.250 1.2719 0.01638 0.00885 -0.0944 0.2749 1.0000
7.500 1.2924 0.01697 0.00936 -0.0934 0.2382 1.0000
7.750 1.3075 0.01814 0.01013 -0.0917 0.1654 1.0000
8.000 1.3109 0.02078 0.01197 -0.0886 0.0668 1.0000
8.250 1.3259 0.02207 0.01321 -0.0867 0.0496 1.0000
8.500 1.3394 0.02340 0.01457 -0.0846 0.0439 1.0000
8.750 1.3525 0.02464 0.01592 -0.0825 0.0404 1.0000
9.000 1.3601 0.02625 0.01758 -0.0798 0.0373 1.0000
9.250 1.3644 0.02801 0.01941 -0.0765 0.0354 1.0000
9.500 1.3732 0.02944 0.02096 -0.0739 0.0342 1.0000
9.750 1.3818 0.03103 0.02268 -0.0713 0.0330 1.0000
10.000 1.3916 0.03273 0.02447 -0.0690 0.0319 1.0000
10.250 1.4025 0.03448 0.02631 -0.0669 0.0307 1.0000
10.500 1.4139 0.03641 0.02826 -0.0651 0.0292 1.0000
10.750 1.4429 0.04067 0.03258 -0.0655 0.0274 1.0000
11.000 1.4563 0.04283 0.03497 -0.0638 0.0271 1.0000
11.250 1.4674 0.04514 0.03755 -0.0618 0.0268 1.0000
11.500 1.4759 0.04782 0.04052 -0.0597 0.0266 1.0000
11.750 1.4805 0.05086 0.04386 -0.0574 0.0265 1.0000
12.000 1.4800 0.05402 0.04731 -0.0548 0.0265 1.0000
12.250 1.4746 0.05708 0.05065 -0.0520 0.0264 1.0000
12.500 1.4657 0.06021 0.05406 -0.0494 0.0263 1.0000
12.750 1.4544 0.06360 0.05772 -0.0472 0.0261 1.0000
13.000 1.4410 0.06730 0.06168 -0.0455 0.0260 1.0000
13.250 1.4257 0.07145 0.06609 -0.0443 0.0259 1.0000
13.500 1.4087 0.07613 0.07101 -0.0438 0.0260 1.0000
13.750 1.3901 0.08125 0.07637 -0.0440 0.0261 1.0000
14.000 1.3702 0.08694 0.08227 -0.0449 0.0263 1.0000
14.250 1.3495 0.09316 0.08869 -0.0466 0.0265 1.0000
14.500 1.3278 0.10001 0.09573 -0.0491 0.0267 1.0000
14.750 1.1598 0.09519 0.09102 -0.0303 0.0280 1.0000
15.000 1.1308 0.10029 0.09632 -0.0327 0.0283 1.0000
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Polar data table (+)
Polar graphs
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