GOE 602 MOD. AIRFOIL (goe602m-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 602 MOD. AIRFOIL (goe602m-il) Reynolds number: 1,000,000 Max Cl/Cd: 122.72 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe602m-il-1000000.txt Download as CSV file: xf-goe602m-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 602 MOD. 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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3056 0.10039 0.09891 -0.0340 1.0000 0.0128
-10.250 -0.3013 0.09531 0.09382 -0.0365 0.9994 0.0128
-9.750 -0.6037 0.02840 0.02607 -0.0947 0.9858 0.0084
-9.500 -0.5807 0.02334 0.02045 -0.0993 0.9838 0.0088
-9.250 -0.5577 0.02162 0.01849 -0.1000 0.9799 0.0091
-9.000 -0.5343 0.01880 0.01525 -0.1014 0.9765 0.0095
-8.750 -0.5065 0.01677 0.01294 -0.1029 0.9745 0.0102
-8.500 -0.4736 0.01632 0.01244 -0.1044 0.9734 0.0107
-8.250 -0.4408 0.01557 0.01157 -0.1059 0.9724 0.0112
-8.000 -0.4075 0.01478 0.01065 -0.1076 0.9715 0.0118
-7.750 -0.3761 0.01402 0.00976 -0.1087 0.9698 0.0124
-7.500 -0.3506 0.01356 0.00920 -0.1083 0.9651 0.0128
-7.250 -0.3225 0.01226 0.00775 -0.1089 0.9620 0.0140
-7.000 -0.2903 0.01207 0.00754 -0.1100 0.9597 0.0148
-6.750 -0.2573 0.01190 0.00734 -0.1111 0.9576 0.0158
-6.500 -0.2299 0.01173 0.00712 -0.1110 0.9527 0.0168
-6.250 -0.2022 0.01122 0.00651 -0.1110 0.9478 0.0177
-6.000 -0.1727 0.01052 0.00576 -0.1116 0.9438 0.0193
-5.750 -0.1459 0.01038 0.00561 -0.1114 0.9375 0.0205
-5.500 -0.1173 0.01017 0.00535 -0.1115 0.9317 0.0219
-5.250 -0.0886 0.01013 0.00526 -0.1115 0.9259 0.0231
-5.000 -0.0629 0.00961 0.00465 -0.1111 0.9192 0.0243
-4.750 -0.0366 0.00896 0.00393 -0.1109 0.9133 0.0263
-4.500 -0.0105 0.00872 0.00366 -0.1105 0.9064 0.0278
-4.000 0.0437 0.00831 0.00316 -0.1101 0.8935 0.0308
-3.750 0.0712 0.00814 0.00292 -0.1099 0.8869 0.0316
-3.500 0.0975 0.00793 0.00268 -0.1095 0.8793 0.0325
-3.250 0.1239 0.00753 0.00216 -0.1091 0.8721 0.0347
-3.000 0.1503 0.00731 0.00190 -0.1087 0.8636 0.0370
-2.750 0.1774 0.00717 0.00171 -0.1084 0.8556 0.0393
-2.500 0.2042 0.00704 0.00154 -0.1081 0.8462 0.0411
-2.250 0.2311 0.00695 0.00139 -0.1078 0.8364 0.0427
-2.000 0.2577 0.00680 0.00123 -0.1074 0.8258 0.0544
-1.750 0.2833 0.00650 0.00112 -0.1070 0.8138 0.1233
-1.500 0.3079 0.00609 0.00103 -0.1065 0.8006 0.2394
-1.250 0.3340 0.00600 0.00101 -0.1060 0.7862 0.2848
-0.750 0.3861 0.00596 0.00095 -0.1051 0.7546 0.3295
-0.500 0.4120 0.00595 0.00094 -0.1047 0.7377 0.3509
-0.250 0.4374 0.00593 0.00094 -0.1041 0.7197 0.3833
0.000 0.4618 0.00587 0.00096 -0.1034 0.6989 0.4450
0.250 0.4858 0.00583 0.00103 -0.1026 0.6740 0.5225
0.500 0.5103 0.00586 0.00108 -0.1018 0.6506 0.5719
0.750 0.5348 0.00590 0.00112 -0.1011 0.6287 0.6093
1.000 0.5594 0.00587 0.00116 -0.1004 0.6104 0.6536
1.250 0.5801 0.00561 0.00126 -0.0988 0.5930 0.8026
1.500 0.6325 0.00543 0.00136 -0.1043 0.5711 1.0000
1.750 0.6572 0.00557 0.00141 -0.1036 0.5526 1.0000
2.000 0.6822 0.00571 0.00148 -0.1029 0.5357 1.0000
2.250 0.7071 0.00587 0.00155 -0.1023 0.5184 1.0000
2.500 0.7319 0.00603 0.00164 -0.1016 0.5008 1.0000
3.000 0.7817 0.00637 0.00183 -0.1004 0.4661 1.0000
3.250 0.8059 0.00659 0.00195 -0.0997 0.4427 1.0000
3.500 0.8303 0.00681 0.00208 -0.0990 0.4202 1.0000
3.750 0.8542 0.00706 0.00222 -0.0982 0.3954 1.0000
4.000 0.8778 0.00734 0.00237 -0.0974 0.3674 1.0000
4.250 0.9012 0.00764 0.00254 -0.0966 0.3366 1.0000
4.500 0.9237 0.00802 0.00275 -0.0957 0.3002 1.0000
5.000 0.9633 0.00921 0.00340 -0.0929 0.1944 1.0000
5.250 0.9780 0.01025 0.00396 -0.0908 0.1080 1.0000
5.500 0.9977 0.01088 0.00441 -0.0894 0.0724 1.0000
5.750 1.0142 0.01181 0.00505 -0.0874 0.0191 1.0000
6.000 1.0374 0.01213 0.00542 -0.0865 0.0170 1.0000
6.250 1.0593 0.01257 0.00588 -0.0854 0.0148 1.0000
6.500 1.0804 0.01306 0.00644 -0.0842 0.0135 1.0000
6.750 1.1028 0.01342 0.00684 -0.0832 0.0128 1.0000
7.000 1.1241 0.01386 0.00732 -0.0820 0.0122 1.0000
7.250 1.1447 0.01434 0.00784 -0.0808 0.0115 1.0000
7.500 1.1646 0.01484 0.00838 -0.0794 0.0108 1.0000
7.750 1.1817 0.01553 0.00912 -0.0776 0.0100 1.0000
8.000 1.1921 0.01667 0.01038 -0.0746 0.0093 1.0000
8.250 1.2106 0.01715 0.01091 -0.0730 0.0091 1.0000
8.500 1.2255 0.01778 0.01159 -0.0708 0.0088 1.0000
8.750 1.2388 0.01840 0.01227 -0.0683 0.0085 1.0000
9.000 1.2509 0.01908 0.01301 -0.0657 0.0082 1.0000
9.250 1.2618 0.01985 0.01383 -0.0629 0.0079 1.0000
9.500 1.2715 0.02073 0.01478 -0.0601 0.0078 1.0000
9.750 1.2820 0.02157 0.01568 -0.0576 0.0075 1.0000
10.000 1.2920 0.02247 0.01664 -0.0551 0.0073 1.0000
10.250 1.3024 0.02335 0.01755 -0.0528 0.0070 1.0000
10.500 1.3070 0.02471 0.01896 -0.0499 0.0068 1.0000
10.750 1.3050 0.02700 0.02134 -0.0464 0.0065 1.0000
11.000 1.3103 0.02912 0.02356 -0.0439 0.0063 1.0000
11.250 1.3212 0.02978 0.02431 -0.0421 0.0062 1.0000
11.500 1.3300 0.03103 0.02566 -0.0403 0.0061 1.0000
11.750 1.3379 0.03242 0.02716 -0.0385 0.0059 1.0000
12.000 1.3440 0.03425 0.02910 -0.0366 0.0058 1.0000
12.250 1.3493 0.03623 0.03120 -0.0348 0.0057 1.0000
12.500 1.3541 0.03816 0.03326 -0.0332 0.0056 1.0000
12.750 1.3570 0.04049 0.03573 -0.0315 0.0055 1.0000
13.000 1.3587 0.04289 0.03827 -0.0301 0.0055 1.0000
13.250 1.3584 0.04561 0.04114 -0.0287 0.0054 1.0000
13.500 1.3575 0.04812 0.04377 -0.0277 0.0053 1.0000
13.750 1.3509 0.05196 0.04782 -0.0266 0.0053 1.0000
14.000 1.3454 0.05528 0.05129 -0.0261 0.0052 1.0000
14.250 1.3375 0.05905 0.05522 -0.0260 0.0052 1.0000
14.500 1.3224 0.06426 0.06066 -0.0263 0.0053 1.0000
14.750 1.3135 0.06843 0.06496 -0.0271 0.0052 1.0000
15.000 1.3017 0.07337 0.07005 -0.0285 0.0051 1.0000
15.250 1.2803 0.08036 0.07727 -0.0308 0.0052 1.0000
15.500 1.2619 0.08716 0.08425 -0.0336 0.0053 1.0000
15.750 1.2498 0.09309 0.09032 -0.0366 0.0051 1.0000
16.000 1.2336 0.10020 0.09758 -0.0404 0.0051 1.0000
16.250 1.2076 0.10980 0.10738 -0.0456 0.0053 1.0000
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