GOE 566 AIRFOIL (goe566-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 566 AIRFOIL (goe566-il) Reynolds number: 1,000,000 Max Cl/Cd: 97.77 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe566-il-1000000.txt Download as CSV file: xf-goe566-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 566 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
------ -------- --------- --------- -------- -------- --------
-11.500 -0.3717 0.11004 0.10841 -0.0234 1.0000 0.0159
-11.250 -0.3714 0.10571 0.10409 -0.0247 1.0000 0.0160
-11.000 -0.8823 0.02810 0.02537 -0.0565 1.0000 0.0121
-10.750 -0.8743 0.02601 0.02302 -0.0545 1.0000 0.0124
-10.500 -0.8772 0.02260 0.01919 -0.0511 1.0000 0.0128
-10.250 -0.8667 0.02148 0.01795 -0.0486 1.0000 0.0131
-10.000 -0.8469 0.02165 0.01818 -0.0471 0.9999 0.0135
-9.750 -0.8108 0.02218 0.01880 -0.0487 0.9988 0.0139
-9.500 -0.7753 0.02247 0.01913 -0.0504 0.9972 0.0143
-9.250 -0.7438 0.02142 0.01791 -0.0519 0.9951 0.0150
-9.000 -0.7148 0.02013 0.01640 -0.0530 0.9926 0.0156
-8.750 -0.6874 0.01849 0.01448 -0.0539 0.9893 0.0162
-8.500 -0.6569 0.01768 0.01360 -0.0551 0.9869 0.0169
-8.250 -0.6230 0.01776 0.01371 -0.0565 0.9851 0.0174
-8.000 -0.5889 0.01777 0.01371 -0.0579 0.9837 0.0179
-7.750 -0.5581 0.01746 0.01333 -0.0588 0.9807 0.0188
-7.500 -0.5273 0.01697 0.01273 -0.0596 0.9771 0.0196
-7.250 -0.4954 0.01658 0.01223 -0.0606 0.9739 0.0202
-7.000 -0.4662 0.01468 0.01010 -0.0617 0.9707 0.0213
-6.750 -0.4377 0.01442 0.00983 -0.0620 0.9647 0.0219
-6.500 -0.4074 0.01427 0.00964 -0.0626 0.9595 0.0227
-6.250 -0.3777 0.01404 0.00937 -0.0631 0.9541 0.0237
-6.000 -0.3515 0.01355 0.00878 -0.0627 0.9464 0.0245
-5.750 -0.3239 0.01320 0.00832 -0.0626 0.9400 0.0252
-5.500 -0.2975 0.01322 0.00828 -0.0622 0.9325 0.0256
-5.250 -0.2745 0.01148 0.00638 -0.0614 0.9258 0.0271
-5.000 -0.2493 0.01107 0.00594 -0.0609 0.9184 0.0278
-4.750 -0.2232 0.01074 0.00556 -0.0605 0.9118 0.0286
-4.500 -0.1973 0.01040 0.00517 -0.0600 0.9048 0.0294
-4.250 -0.1711 0.01012 0.00485 -0.0595 0.8982 0.0303
-4.000 -0.1453 0.00975 0.00443 -0.0590 0.8908 0.0310
-3.750 -0.1196 0.00943 0.00404 -0.0584 0.8824 0.0316
-3.500 -0.0937 0.00917 0.00373 -0.0579 0.8732 0.0321
-3.250 -0.0676 0.00898 0.00348 -0.0573 0.8640 0.0325
-3.000 -0.0435 0.00839 0.00283 -0.0565 0.8541 0.0338
-2.750 -0.0181 0.00806 0.00244 -0.0559 0.8442 0.0348
-2.500 0.0078 0.00785 0.00218 -0.0553 0.8340 0.0358
-2.250 0.0340 0.00767 0.00195 -0.0548 0.8225 0.0368
-2.000 0.0603 0.00752 0.00176 -0.0543 0.8097 0.0379
-1.750 0.0867 0.00740 0.00159 -0.0539 0.7970 0.0395
-1.500 0.1132 0.00731 0.00145 -0.0534 0.7843 0.0409
-1.250 0.1397 0.00720 0.00129 -0.0530 0.7723 0.0433
-1.000 0.1662 0.00708 0.00115 -0.0526 0.7608 0.0488
-0.750 0.1922 0.00688 0.00104 -0.0521 0.7485 0.0852
-0.500 0.2173 0.00657 0.00099 -0.0516 0.7360 0.1794
-0.250 0.2416 0.00623 0.00094 -0.0510 0.7209 0.2915
0.000 0.2599 0.00537 0.00091 -0.0494 0.7015 0.5936
0.250 0.2797 0.00499 0.00093 -0.0476 0.6793 0.7488
0.500 0.2999 0.00472 0.00098 -0.0456 0.6613 0.8601
0.750 0.3469 0.00469 0.00108 -0.0495 0.6424 0.9578
1.000 0.3924 0.00482 0.00113 -0.0533 0.6215 0.9770
1.250 0.4347 0.00500 0.00119 -0.0564 0.5975 0.9888
1.500 0.4796 0.00519 0.00124 -0.0602 0.5656 0.9962
1.750 0.5198 0.00544 0.00127 -0.0630 0.5114 1.0000
2.000 0.5402 0.00578 0.00134 -0.0616 0.4509 1.0000
2.250 0.5614 0.00609 0.00145 -0.0603 0.4051 1.0000
2.500 0.5835 0.00636 0.00155 -0.0592 0.3676 1.0000
2.750 0.6057 0.00663 0.00166 -0.0581 0.3322 1.0000
3.000 0.6279 0.00691 0.00179 -0.0570 0.2978 1.0000
3.250 0.6505 0.00717 0.00192 -0.0559 0.2712 1.0000
3.500 0.6737 0.00739 0.00205 -0.0550 0.2526 1.0000
3.750 0.6973 0.00758 0.00218 -0.0542 0.2395 1.0000
4.000 0.7213 0.00775 0.00230 -0.0534 0.2300 1.0000
4.250 0.7455 0.00790 0.00244 -0.0526 0.2224 1.0000
4.500 0.7694 0.00808 0.00258 -0.0518 0.2137 1.0000
4.750 0.7939 0.00822 0.00272 -0.0511 0.2063 1.0000
5.000 0.8178 0.00842 0.00288 -0.0503 0.1965 1.0000
5.250 0.8418 0.00861 0.00303 -0.0496 0.1848 1.0000
5.500 0.8652 0.00885 0.00319 -0.0487 0.1662 1.0000
5.750 0.8857 0.00934 0.00346 -0.0475 0.1224 1.0000
6.000 0.9060 0.00986 0.00382 -0.0462 0.0945 1.0000
6.250 0.9287 0.01018 0.00410 -0.0452 0.0850 1.0000
6.500 0.9513 0.01050 0.00439 -0.0443 0.0767 1.0000
6.750 0.9744 0.01079 0.00466 -0.0434 0.0672 1.0000
7.000 0.9941 0.01138 0.00506 -0.0421 0.0397 1.0000
7.250 1.0158 0.01181 0.00547 -0.0410 0.0326 1.0000
7.500 1.0371 0.01229 0.00594 -0.0398 0.0284 1.0000
7.750 1.0594 0.01265 0.00634 -0.0389 0.0264 1.0000
8.000 1.0818 0.01300 0.00673 -0.0379 0.0244 1.0000
8.250 1.1020 0.01357 0.00731 -0.0367 0.0217 1.0000
8.500 1.1237 0.01397 0.00775 -0.0357 0.0204 1.0000
8.750 1.1456 0.01433 0.00815 -0.0347 0.0191 1.0000
9.000 1.1668 0.01476 0.00860 -0.0337 0.0178 1.0000
9.250 1.1833 0.01560 0.00950 -0.0319 0.0162 1.0000
9.500 1.2054 0.01590 0.00983 -0.0310 0.0155 1.0000
9.750 1.2261 0.01631 0.01028 -0.0299 0.0147 1.0000
10.000 1.2460 0.01677 0.01077 -0.0288 0.0139 1.0000
10.250 1.2640 0.01736 0.01138 -0.0273 0.0131 1.0000
10.500 1.2745 0.01847 0.01260 -0.0247 0.0123 1.0000
10.750 1.2927 0.01895 0.01313 -0.0233 0.0120 1.0000
11.000 1.3088 0.01952 0.01377 -0.0216 0.0116 1.0000
11.250 1.3219 0.02012 0.01443 -0.0194 0.0112 1.0000
11.500 1.3342 0.02073 0.01509 -0.0171 0.0108 1.0000
11.750 1.3461 0.02138 0.01579 -0.0148 0.0104 1.0000
12.000 1.3560 0.02217 0.01664 -0.0124 0.0101 1.0000
12.250 1.3622 0.02322 0.01776 -0.0097 0.0098 1.0000
12.500 1.3561 0.02513 0.01980 -0.0060 0.0093 1.0000
12.750 1.3648 0.02615 0.02091 -0.0041 0.0091 1.0000
13.000 1.3706 0.02744 0.02230 -0.0021 0.0090 1.0000
13.250 1.3804 0.02848 0.02342 -0.0007 0.0088 1.0000
13.500 1.3847 0.03000 0.02504 0.0010 0.0086 1.0000
13.750 1.3933 0.03124 0.02636 0.0022 0.0084 1.0000
14.000 1.3947 0.03317 0.02840 0.0036 0.0082 1.0000
14.250 1.3946 0.03535 0.03070 0.0047 0.0081 1.0000
14.500 1.3996 0.03716 0.03259 0.0053 0.0079 1.0000
14.750 1.4009 0.03944 0.03496 0.0058 0.0077 1.0000
15.000 1.3973 0.04240 0.03803 0.0061 0.0076 1.0000
15.250 1.4004 0.04475 0.04045 0.0059 0.0074 1.0000
15.500 1.3930 0.04847 0.04428 0.0054 0.0073 1.0000
15.750 1.3839 0.05264 0.04858 0.0045 0.0073 1.0000
16.000 1.3724 0.05735 0.05341 0.0030 0.0071 1.0000
16.250 1.3639 0.06195 0.05814 0.0014 0.0072 1.0000
16.500 1.3490 0.06776 0.06409 -0.0010 0.0071 1.0000
16.750 1.3316 0.07425 0.07071 -0.0040 0.0070 1.0000
17.000 1.3193 0.08018 0.07676 -0.0068 0.0070 1.0000
17.250 1.3033 0.08683 0.08354 -0.0100 0.0070 1.0000
17.500 1.2834 0.09429 0.09114 -0.0136 0.0070 1.0000
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