GOE 364 AIRFOIL (goe364-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 364 AIRFOIL (goe364-il) Reynolds number: 500,000 Max Cl/Cd: 107.79 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe364-il-500000.txt Download as CSV file: xf-goe364-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 364 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.2293 0.11924 0.11700 -0.0327 1.0000 0.0184
-10.500 -0.2280 0.11687 0.11465 -0.0324 1.0000 0.0189
-10.250 -0.2276 0.11458 0.11240 -0.0319 1.0000 0.0193
-10.000 -0.2224 0.11152 0.10935 -0.0338 0.9993 0.0198
-9.750 -0.2072 0.10721 0.10504 -0.0406 0.9965 0.0200
-9.500 -0.1948 0.10287 0.10071 -0.0477 0.9922 0.0200
-9.250 -0.1742 0.09829 0.09612 -0.0495 0.9889 0.0202
-9.000 -0.1521 0.09462 0.09245 -0.0522 0.9854 0.0204
-8.750 -0.1330 0.09109 0.08893 -0.0559 0.9796 0.0207
-8.500 -0.1137 0.08761 0.08544 -0.0600 0.9730 0.0212
-8.250 -0.0947 0.08406 0.08188 -0.0644 0.9641 0.0219
-8.000 -0.0675 0.07930 0.07710 -0.0736 0.9563 0.0234
-7.750 -0.0458 0.07375 0.07150 -0.0871 0.9314 0.0236
-7.500 0.0337 0.05560 0.05300 -0.0847 0.8238 0.0244
-7.250 0.0364 0.05330 0.05062 -0.0846 0.8067 0.0247
-7.000 0.0135 0.06373 0.06112 -0.0957 0.8461 0.0245
-6.750 0.0229 0.06143 0.05869 -0.0969 0.8217 0.0249
-6.500 0.0327 0.05903 0.05617 -0.0983 0.8042 0.0255
-6.250 0.0441 0.05640 0.05344 -0.1002 0.7901 0.0263
-5.750 0.0745 0.04746 0.04418 -0.1087 0.7673 0.0281
-5.500 0.0895 0.04562 0.04229 -0.1084 0.7581 0.0284
-5.250 0.1064 0.04375 0.04033 -0.1085 0.7491 0.0289
-5.000 0.1252 0.04160 0.03810 -0.1092 0.7405 0.0297
-4.750 0.1559 0.03664 0.03263 -0.1121 0.7327 0.0327
-4.500 0.1704 0.03378 0.02976 -0.1120 0.7250 0.0332
-4.250 0.1899 0.03240 0.02833 -0.1117 0.7170 0.0337
-4.000 0.2111 0.03090 0.02673 -0.1115 0.7098 0.0344
-3.750 0.2337 0.02912 0.02481 -0.1113 0.7022 0.0359
-3.500 0.2578 0.02542 0.02060 -0.1107 0.6961 0.0392
-3.250 0.2801 0.02430 0.01947 -0.1104 0.6883 0.0400
-3.000 0.3033 0.02336 0.01841 -0.1099 0.6811 0.0414
-2.750 0.3279 0.02121 0.01582 -0.1088 0.6739 0.0464
-2.500 0.3511 0.02018 0.01475 -0.1083 0.6660 0.0474
-2.250 0.3755 0.01939 0.01389 -0.1078 0.6580 0.0493
-2.000 0.4004 0.01825 0.01237 -0.1068 0.6499 0.0553
-1.750 0.4247 0.01741 0.01152 -0.1063 0.6407 0.0570
-1.250 0.4744 0.01611 0.00996 -0.1050 0.6208 0.0676
-1.000 0.5000 0.01585 0.00958 -0.1043 0.6109 0.0730
-0.750 0.5242 0.01505 0.00866 -0.1037 0.5998 0.0804
-0.500 0.5534 0.01267 0.00558 -0.1015 0.5897 0.0460
-0.250 0.5792 0.01239 0.00520 -0.1008 0.5781 0.0457
0.000 0.6042 0.01191 0.00463 -0.1000 0.5656 0.0452
0.250 0.6291 0.01143 0.00410 -0.0992 0.5522 0.0448
0.500 0.6540 0.01115 0.00376 -0.0984 0.5388 0.0447
0.750 0.6788 0.01097 0.00352 -0.0976 0.5264 0.0450
1.000 0.7034 0.01087 0.00335 -0.0968 0.5151 0.0453
1.250 0.7277 0.01076 0.00319 -0.0960 0.5039 0.0457
1.500 0.7521 0.01060 0.00301 -0.0952 0.4935 0.0475
1.750 0.7766 0.01060 0.00296 -0.0944 0.4843 0.0493
2.000 0.8019 0.01061 0.00293 -0.0938 0.4758 0.0509
2.250 0.8268 0.01067 0.00294 -0.0931 0.4684 0.0532
2.500 0.8522 0.01070 0.00296 -0.0925 0.4612 0.0582
2.750 0.9216 0.00912 0.00336 -0.1023 0.4522 1.0000
3.000 0.9462 0.00926 0.00344 -0.1016 0.4456 1.0000
3.250 0.9696 0.00947 0.00355 -0.1006 0.4389 1.0000
3.500 0.9942 0.00960 0.00365 -0.0999 0.4326 1.0000
3.750 1.0180 0.00977 0.00378 -0.0991 0.4261 1.0000
4.000 1.0416 0.00997 0.00392 -0.0982 0.4203 1.0000
4.250 1.0660 0.01010 0.00404 -0.0975 0.4141 1.0000
4.500 1.0891 0.01031 0.00420 -0.0966 0.4077 1.0000
4.750 1.1130 0.01046 0.00435 -0.0958 0.4011 1.0000
5.000 1.1363 0.01064 0.00449 -0.0949 0.3938 1.0000
5.250 1.1593 0.01083 0.00466 -0.0940 0.3867 1.0000
5.500 1.1825 0.01099 0.00483 -0.0931 0.3788 1.0000
5.750 1.2049 0.01120 0.00500 -0.0921 0.3706 1.0000
6.000 1.2272 0.01139 0.00517 -0.0911 0.3606 1.0000
6.250 1.2493 0.01159 0.00537 -0.0900 0.3494 1.0000
6.500 1.2700 0.01184 0.00557 -0.0888 0.3354 1.0000
6.750 1.2896 0.01214 0.00580 -0.0873 0.3187 1.0000
7.000 1.3084 0.01249 0.00607 -0.0858 0.3031 1.0000
7.250 1.3266 0.01286 0.00638 -0.0842 0.2897 1.0000
7.500 1.3440 0.01326 0.00672 -0.0824 0.2783 1.0000
7.750 1.3606 0.01368 0.00709 -0.0805 0.2684 1.0000
8.000 1.3772 0.01403 0.00744 -0.0786 0.2608 1.0000
8.250 1.3917 0.01445 0.00783 -0.0763 0.2542 1.0000
8.500 1.4075 0.01484 0.00822 -0.0743 0.2489 1.0000
8.750 1.4239 0.01521 0.00862 -0.0725 0.2438 1.0000
9.000 1.4378 0.01571 0.00909 -0.0703 0.2386 1.0000
9.250 1.4539 0.01612 0.00954 -0.0685 0.2337 1.0000
9.500 1.4702 0.01654 0.00999 -0.0668 0.2288 1.0000
9.750 1.4828 0.01713 0.01056 -0.0647 0.2231 1.0000
10.000 1.4990 0.01757 0.01106 -0.0631 0.2185 1.0000
10.250 1.5145 0.01805 0.01158 -0.0615 0.2131 1.0000
10.500 1.5265 0.01872 0.01224 -0.0595 0.2083 1.0000
10.750 1.5417 0.01925 0.01283 -0.0580 0.2040 1.0000
11.000 1.5570 0.01979 0.01343 -0.0566 0.1989 1.0000
11.250 1.5678 0.02059 0.01423 -0.0547 0.1933 1.0000
11.500 1.5828 0.02118 0.01489 -0.0534 0.1877 1.0000
11.750 1.5955 0.02194 0.01568 -0.0519 0.1817 1.0000
12.000 1.6059 0.02287 0.01663 -0.0503 0.1763 1.0000
12.250 1.6195 0.02363 0.01747 -0.0491 0.1700 1.0000
12.500 1.6273 0.02483 0.01865 -0.0475 0.1634 1.0000
12.750 1.6391 0.02580 0.01968 -0.0464 0.1557 1.0000
13.000 1.6458 0.02718 0.02107 -0.0450 0.1483 1.0000
13.250 1.6524 0.02863 0.02254 -0.0437 0.1401 1.0000
13.500 1.6569 0.03030 0.02422 -0.0425 0.1318 1.0000
13.750 1.6583 0.03231 0.02623 -0.0412 0.1239 1.0000
14.000 1.6614 0.03422 0.02817 -0.0401 0.1168 1.0000
14.250 1.6612 0.03649 0.03046 -0.0391 0.1100 1.0000
14.500 1.6596 0.03898 0.03297 -0.0381 0.1027 1.0000
14.750 1.6588 0.04146 0.03550 -0.0374 0.0966 1.0000
15.000 1.6532 0.04450 0.03854 -0.0366 0.0897 1.0000
15.250 1.6469 0.04772 0.04177 -0.0361 0.0808 1.0000
15.500 1.6410 0.05100 0.04508 -0.0357 0.0735 1.0000
15.750 1.6292 0.05506 0.04914 -0.0355 0.0635 1.0000
16.000 1.6111 0.06004 0.05409 -0.0356 0.0512 1.0000
16.250 1.5889 0.06571 0.05972 -0.0361 0.0382 1.0000
16.500 1.5626 0.07220 0.06621 -0.0369 0.0274 1.0000
16.750 1.5439 0.07790 0.07197 -0.0379 0.0236 1.0000
17.000 1.5271 0.08347 0.07762 -0.0391 0.0212 1.0000
17.250 1.5157 0.08841 0.08267 -0.0402 0.0203 1.0000
17.500 1.5025 0.09369 0.08806 -0.0415 0.0195 1.0000
17.750 1.4891 0.09907 0.09356 -0.0430 0.0189 1.0000
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