GOE 584 AIRFOIL (goe584-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 584 AIRFOIL (goe584-il) Reynolds number: 200,000 Max Cl/Cd: 78.07 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe584-il-200000.txt Download as CSV file: xf-goe584-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 584 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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.2722 0.11160 0.10789 -0.0431 1.0000 0.0635
-10.500 -0.2827 0.10884 0.10519 -0.0457 1.0000 0.0669
-10.250 -0.3125 0.10600 0.10247 -0.0508 1.0000 0.0677
-10.000 -0.2980 0.10201 0.09851 -0.0476 1.0000 0.0686
-9.750 -0.2899 0.10023 0.09678 -0.0447 1.0000 0.0695
-9.500 -0.3023 0.09976 0.09643 -0.0407 0.9993 0.0700
-9.250 -0.2779 0.09599 0.09264 -0.0449 0.9943 0.0724
-9.000 -0.2802 0.08901 0.08566 -0.0635 0.9796 0.0780
-8.750 -0.2613 0.08372 0.08037 -0.0652 0.9741 0.0794
-8.500 -0.2294 0.08142 0.07804 -0.0649 0.9710 0.0812
-8.250 -0.2065 0.07804 0.07463 -0.0689 0.9629 0.0843
-8.000 -0.2113 0.06637 0.06283 -0.0947 0.9424 0.0911
-7.750 -0.1777 0.06518 0.06168 -0.0919 0.9395 0.0926
-7.500 -0.1538 0.06336 0.05983 -0.0922 0.9288 0.0955
-7.250 -0.1634 0.05467 0.05075 -0.1061 0.9082 0.1046
-7.000 -0.1420 0.05300 0.04912 -0.1047 0.8983 0.1059
-6.750 -0.1206 0.05146 0.04755 -0.1042 0.8897 0.1083
-6.250 -0.1063 0.04521 0.04090 -0.1060 0.8648 0.1208
-6.000 -0.0870 0.04373 0.03938 -0.1052 0.8565 0.1236
-5.750 -0.0807 0.04065 0.03586 -0.1058 0.8452 0.1348
-5.500 -0.0815 0.02859 0.02221 -0.1045 0.8375 0.0898
-5.250 -0.0632 0.02642 0.01979 -0.1033 0.8281 0.0893
-5.000 -0.0401 0.02497 0.01797 -0.1025 0.8214 0.0898
-4.750 -0.0188 0.02352 0.01628 -0.1014 0.8128 0.0898
-4.500 0.0057 0.02231 0.01478 -0.1007 0.8060 0.0900
-4.250 0.0289 0.02092 0.01316 -0.0999 0.7986 0.0910
-4.000 0.0536 0.01975 0.01188 -0.0994 0.7912 0.0924
-3.750 0.0804 0.01897 0.01096 -0.0990 0.7855 0.0935
-3.500 0.1050 0.01834 0.01027 -0.0983 0.7774 0.0945
-3.250 0.1322 0.01776 0.00957 -0.0979 0.7713 0.0960
-3.000 0.1580 0.01734 0.00908 -0.0973 0.7644 0.0981
-2.750 0.1843 0.01692 0.00858 -0.0968 0.7576 0.1003
-2.500 0.2123 0.01651 0.00805 -0.0965 0.7524 0.1021
-2.250 0.2372 0.01619 0.00771 -0.0957 0.7448 0.1037
-2.000 0.2632 0.01558 0.00713 -0.0952 0.7387 0.1066
-1.750 0.2898 0.01530 0.00685 -0.0948 0.7332 0.1106
-1.500 0.3146 0.01510 0.00667 -0.0941 0.7259 0.1152
-1.250 0.3412 0.01477 0.00633 -0.0936 0.7203 0.1207
-1.000 0.3664 0.01457 0.00618 -0.0929 0.7141 0.1287
-0.750 0.3914 0.01432 0.00601 -0.0922 0.7073 0.1435
-0.500 0.4169 0.01382 0.00579 -0.0916 0.7022 0.2171
-0.250 0.4356 0.01312 0.00584 -0.0902 0.6951 0.4078
0.000 0.5112 0.01167 0.00588 -0.0988 0.6886 0.9635
0.250 0.5740 0.01168 0.00570 -0.1058 0.6823 1.0000
0.500 0.5961 0.01178 0.00573 -0.1046 0.6750 1.0000
0.750 0.6212 0.01186 0.00565 -0.1039 0.6694 1.0000
1.000 0.6435 0.01200 0.00575 -0.1028 0.6624 1.0000
1.250 0.6674 0.01209 0.00576 -0.1019 0.6559 1.0000
1.500 0.6930 0.01220 0.00574 -0.1012 0.6503 1.0000
1.750 0.7148 0.01235 0.00589 -0.1000 0.6428 1.0000
2.000 0.7402 0.01244 0.00588 -0.0993 0.6368 1.0000
2.250 0.7634 0.01260 0.00601 -0.0983 0.6300 1.0000
2.500 0.7873 0.01272 0.00608 -0.0974 0.6229 1.0000
2.750 0.8132 0.01284 0.00611 -0.0968 0.6170 1.0000
3.000 0.8351 0.01300 0.00629 -0.0956 0.6090 1.0000
3.250 0.8612 0.01310 0.00630 -0.0951 0.6027 1.0000
3.500 0.8833 0.01328 0.00650 -0.0939 0.5949 1.0000
3.750 0.9082 0.01338 0.00655 -0.0932 0.5877 1.0000
4.000 0.9314 0.01355 0.00672 -0.0922 0.5801 1.0000
4.250 0.9555 0.01367 0.00681 -0.0913 0.5722 1.0000
4.500 0.9791 0.01383 0.00695 -0.0904 0.5643 1.0000
4.750 1.0026 0.01395 0.00707 -0.0894 0.5558 1.0000
5.000 1.0258 0.01411 0.00723 -0.0884 0.5472 1.0000
5.250 1.0494 0.01421 0.00729 -0.0875 0.5378 1.0000
5.500 1.0704 0.01432 0.00742 -0.0860 0.5263 1.0000
5.750 1.0925 0.01442 0.00749 -0.0848 0.5148 1.0000
6.000 1.1150 0.01453 0.00755 -0.0836 0.5037 1.0000
6.250 1.1351 0.01471 0.00779 -0.0821 0.4921 1.0000
6.500 1.1564 0.01490 0.00798 -0.0809 0.4809 1.0000
6.750 1.1782 0.01511 0.00813 -0.0797 0.4700 1.0000
7.000 1.1976 0.01534 0.00840 -0.0781 0.4576 1.0000
7.250 1.2170 0.01559 0.00869 -0.0766 0.4451 1.0000
7.500 1.2361 0.01587 0.00896 -0.0750 0.4325 1.0000
7.750 1.2544 0.01618 0.00923 -0.0733 0.4196 1.0000
8.000 1.2720 0.01653 0.00953 -0.0715 0.4067 1.0000
8.250 1.2882 0.01689 0.00993 -0.0695 0.3932 1.0000
8.500 1.3038 0.01730 0.01035 -0.0675 0.3799 1.0000
8.750 1.3182 0.01775 0.01079 -0.0653 0.3667 1.0000
9.000 1.3306 0.01824 0.01126 -0.0627 0.3531 1.0000
9.250 1.3393 0.01876 0.01175 -0.0596 0.3392 1.0000
9.500 1.3463 0.01935 0.01229 -0.0563 0.3254 1.0000
9.750 1.3527 0.02003 0.01292 -0.0530 0.3114 1.0000
10.000 1.3587 0.02076 0.01364 -0.0500 0.2973 1.0000
10.250 1.3650 0.02156 0.01445 -0.0471 0.2835 1.0000
10.500 1.3706 0.02246 0.01536 -0.0444 0.2699 1.0000
10.750 1.3757 0.02347 0.01637 -0.0418 0.2566 1.0000
11.000 1.3801 0.02460 0.01748 -0.0394 0.2438 1.0000
11.250 1.3836 0.02587 0.01873 -0.0371 0.2314 1.0000
11.750 1.3911 0.02864 0.02150 -0.0331 0.2082 1.0000
12.000 1.3958 0.03010 0.02298 -0.0314 0.1984 1.0000
12.250 1.3978 0.03180 0.02462 -0.0297 0.1896 1.0000
12.500 1.4033 0.03332 0.02622 -0.0284 0.1804 1.0000
12.750 1.4063 0.03507 0.02799 -0.0270 0.1720 1.0000
13.000 1.4093 0.03689 0.02983 -0.0258 0.1642 1.0000
13.250 1.4132 0.03869 0.03169 -0.0248 0.1571 1.0000
13.500 1.4152 0.04070 0.03373 -0.0238 0.1501 1.0000
13.750 1.4184 0.04269 0.03579 -0.0229 0.1433 1.0000
14.000 1.4185 0.04503 0.03816 -0.0222 0.1360 1.0000
14.250 1.4201 0.04732 0.04055 -0.0216 0.1280 1.0000
14.500 1.4163 0.05024 0.04346 -0.0212 0.1202 1.0000
14.750 1.4137 0.05319 0.04649 -0.0209 0.1099 1.0000
15.000 1.4087 0.05654 0.04988 -0.0209 0.0985 1.0000
15.250 1.3991 0.06055 0.05388 -0.0210 0.0857 1.0000
15.500 1.3888 0.06477 0.05808 -0.0213 0.0733 1.0000
15.750 1.3774 0.06926 0.06254 -0.0218 0.0641 1.0000
16.000 1.3687 0.07352 0.06683 -0.0223 0.0586 1.0000
16.250 1.3597 0.07790 0.07124 -0.0230 0.0549 1.0000
16.500 1.3526 0.08214 0.07554 -0.0238 0.0518 1.0000
16.750 1.3419 0.08696 0.08037 -0.0249 0.0494 1.0000
17.000 1.3371 0.09098 0.08448 -0.0258 0.0475 1.0000
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