GOE 528 AIRFOIL (goe528-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 528 AIRFOIL (goe528-il) Reynolds number: 500,000 Max Cl/Cd: 110.48 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe528-il-500000.txt Download as CSV file: xf-goe528-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 528 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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.0715 0.09088 0.08867 -0.0749 0.9504 0.0286
-10.250 -0.1752 0.10434 0.10209 -0.0552 0.9846 0.0259
-10.000 -0.1612 0.10079 0.09854 -0.0585 0.9738 0.0268
-9.750 -0.1568 0.09412 0.09186 -0.0691 0.9600 0.0286
-9.500 -0.1386 0.08931 0.08703 -0.0732 0.9513 0.0289
-9.250 -0.1093 0.08610 0.08380 -0.0771 0.9445 0.0293
-9.000 -0.0778 0.08239 0.08004 -0.0834 0.9369 0.0300
-8.750 -0.0446 0.07799 0.07558 -0.0919 0.9270 0.0311
-8.500 -0.0308 0.06849 0.06594 -0.1097 0.9008 0.0336
-8.250 -0.0132 0.06629 0.06366 -0.1104 0.8859 0.0340
-8.000 -0.0009 0.06452 0.06182 -0.1107 0.8708 0.0344
-7.750 0.0031 0.06252 0.05976 -0.1108 0.8562 0.0347
-7.500 0.0069 0.06051 0.05769 -0.1112 0.8434 0.0353
-7.250 0.0114 0.05787 0.05499 -0.1127 0.8311 0.0361
-7.000 -0.0057 0.04512 0.04196 -0.1264 0.8168 0.0393
-6.750 0.0089 0.04419 0.04102 -0.1253 0.8082 0.0397
-6.500 0.0246 0.04328 0.04008 -0.1245 0.7990 0.0402
-6.250 0.0407 0.04188 0.03861 -0.1244 0.7905 0.0409
-6.000 0.0434 0.03320 0.02921 -0.1281 0.7815 0.0460
-5.750 0.0629 0.03161 0.02765 -0.1277 0.7733 0.0465
-5.500 0.0832 0.03049 0.02648 -0.1273 0.7646 0.0472
-5.250 0.1038 0.02920 0.02511 -0.1269 0.7561 0.0482
-5.000 0.1199 0.02584 0.02110 -0.1263 0.7477 0.0540
-4.750 0.1422 0.02457 0.01985 -0.1260 0.7390 0.0549
-4.500 0.1649 0.02358 0.01879 -0.1254 0.7298 0.0561
-4.250 0.1790 0.01608 0.01001 -0.1227 0.7224 0.0409
-4.000 0.2038 0.01527 0.00902 -0.1220 0.7130 0.0414
-3.750 0.2287 0.01430 0.00785 -0.1213 0.7030 0.0414
-3.500 0.2540 0.01360 0.00697 -0.1206 0.6933 0.0416
-3.250 0.2796 0.01301 0.00626 -0.1199 0.6824 0.0420
-3.000 0.3052 0.01252 0.00566 -0.1193 0.6718 0.0424
-2.750 0.3307 0.01214 0.00517 -0.1186 0.6610 0.0431
-2.500 0.3565 0.01183 0.00479 -0.1180 0.6494 0.0441
-2.250 0.3822 0.01156 0.00442 -0.1174 0.6384 0.0449
-2.000 0.4077 0.01134 0.00411 -0.1167 0.6277 0.0454
-1.750 0.4325 0.01091 0.00363 -0.1160 0.6169 0.0464
-1.500 0.4578 0.01067 0.00336 -0.1153 0.6070 0.0478
-1.250 0.4832 0.01055 0.00318 -0.1147 0.5975 0.0493
-1.000 0.5093 0.01044 0.00304 -0.1142 0.5883 0.0512
-0.750 0.5349 0.01038 0.00290 -0.1136 0.5801 0.0538
-0.500 0.5609 0.01024 0.00277 -0.1131 0.5719 0.0579
-0.250 0.5866 0.01021 0.00267 -0.1126 0.5646 0.0640
0.000 0.6125 0.01002 0.00260 -0.1121 0.5575 0.0954
0.250 0.6359 0.00960 0.00265 -0.1114 0.5506 0.2672
0.500 0.6595 0.00927 0.00275 -0.1107 0.5444 0.4303
0.750 0.6732 0.00837 0.00288 -0.1078 0.5384 0.7861
1.000 0.7500 0.00830 0.00297 -0.1182 0.5303 1.0000
1.250 0.7749 0.00839 0.00302 -0.1175 0.5244 1.0000
1.500 0.7993 0.00853 0.00307 -0.1167 0.5184 1.0000
1.750 0.8238 0.00867 0.00314 -0.1160 0.5126 1.0000
2.000 0.8488 0.00877 0.00321 -0.1153 0.5067 1.0000
2.250 0.8731 0.00893 0.00328 -0.1145 0.5009 1.0000
2.500 0.8979 0.00906 0.00337 -0.1138 0.4953 1.0000
2.750 0.9227 0.00917 0.00346 -0.1132 0.4892 1.0000
3.000 0.9468 0.00934 0.00355 -0.1124 0.4833 1.0000
3.250 0.9716 0.00945 0.00365 -0.1118 0.4773 1.0000
3.500 0.9961 0.00958 0.00375 -0.1110 0.4710 1.0000
3.750 1.0200 0.00977 0.00387 -0.1103 0.4651 1.0000
4.000 1.0448 0.00986 0.00398 -0.1097 0.4590 1.0000
4.250 1.0688 0.01002 0.00411 -0.1089 0.4529 1.0000
4.500 1.0929 0.01019 0.00425 -0.1082 0.4473 1.0000
4.750 1.1173 0.01031 0.00438 -0.1075 0.4411 1.0000
5.000 1.1406 0.01050 0.00453 -0.1067 0.4352 1.0000
5.250 1.1646 0.01065 0.00469 -0.1060 0.4294 1.0000
5.500 1.1881 0.01081 0.00485 -0.1052 0.4228 1.0000
5.750 1.2106 0.01103 0.00503 -0.1042 0.4165 1.0000
6.000 1.2341 0.01117 0.00520 -0.1034 0.4093 1.0000
6.250 1.2551 0.01141 0.00539 -0.1022 0.4014 1.0000
6.500 1.2779 0.01157 0.00558 -0.1013 0.3932 1.0000
6.750 1.2983 0.01183 0.00580 -0.1001 0.3857 1.0000
7.000 1.3207 0.01201 0.00602 -0.0991 0.3783 1.0000
7.250 1.3402 0.01230 0.00626 -0.0977 0.3710 1.0000
7.500 1.3614 0.01250 0.00651 -0.0966 0.3633 1.0000
8.000 1.3976 0.01304 0.00705 -0.0932 0.3477 1.0000
8.500 1.4304 0.01367 0.00768 -0.0893 0.3308 1.0000
8.750 1.4452 0.01407 0.00805 -0.0872 0.3230 1.0000
9.000 1.4627 0.01439 0.00840 -0.0856 0.3152 1.0000
9.250 1.4769 0.01483 0.00883 -0.0835 0.3071 1.0000
9.500 1.4928 0.01523 0.00926 -0.0817 0.2986 1.0000
9.750 1.5067 0.01572 0.00974 -0.0797 0.2908 1.0000
10.000 1.5215 0.01620 0.01024 -0.0779 0.2830 1.0000
10.250 1.5346 0.01676 0.01081 -0.0759 0.2751 1.0000
10.500 1.5466 0.01739 0.01144 -0.0739 0.2660 1.0000
10.750 1.5595 0.01801 0.01209 -0.0721 0.2573 1.0000
11.000 1.5684 0.01886 0.01291 -0.0699 0.2482 1.0000
11.250 1.5812 0.01956 0.01365 -0.0682 0.2393 1.0000
11.500 1.5902 0.02049 0.01458 -0.0663 0.2294 1.0000
11.750 1.5979 0.02154 0.01562 -0.0643 0.2205 1.0000
12.000 1.6080 0.02251 0.01662 -0.0626 0.2112 1.0000
12.250 1.6149 0.02372 0.01783 -0.0608 0.2029 1.0000
12.500 1.6215 0.02500 0.01912 -0.0591 0.1932 1.0000
12.750 1.6264 0.02647 0.02059 -0.0574 0.1817 1.0000
13.000 1.6292 0.02814 0.02226 -0.0557 0.1699 1.0000
13.250 1.6289 0.03013 0.02422 -0.0540 0.1559 1.0000
13.500 1.6225 0.03272 0.02673 -0.0521 0.1374 1.0000
13.750 1.6102 0.03596 0.02985 -0.0502 0.1123 1.0000
14.000 1.5948 0.03969 0.03349 -0.0486 0.0947 1.0000
14.250 1.5855 0.04303 0.03683 -0.0474 0.0868 1.0000
14.500 1.5775 0.04641 0.04025 -0.0466 0.0817 1.0000
14.750 1.5726 0.04960 0.04351 -0.0461 0.0775 1.0000
15.000 1.5692 0.05270 0.04669 -0.0457 0.0743 1.0000
15.250 1.5622 0.05631 0.05036 -0.0454 0.0712 1.0000
15.500 1.5539 0.06019 0.05431 -0.0454 0.0681 1.0000
15.750 1.5547 0.06303 0.05725 -0.0454 0.0654 1.0000
16.000 1.5500 0.06659 0.06088 -0.0455 0.0624 1.0000
16.250 1.5410 0.07078 0.06513 -0.0459 0.0596 1.0000
16.500 1.5389 0.07415 0.06859 -0.0462 0.0566 1.0000
16.750 1.5341 0.07791 0.07242 -0.0467 0.0532 1.0000
17.000 1.5237 0.08250 0.07705 -0.0474 0.0501 1.0000
17.250 1.5205 0.08619 0.08082 -0.0480 0.0462 1.0000
17.500 1.5089 0.09114 0.08580 -0.0491 0.0425 1.0000
17.750 1.5026 0.09538 0.09011 -0.0500 0.0389 1.0000
18.000 1.4904 0.10061 0.09537 -0.0514 0.0358 1.0000
18.250 1.4823 0.10528 0.10012 -0.0527 0.0327 1.0000
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