GOE 505 AIRFOIL (goe505-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 505 AIRFOIL (goe505-il) Reynolds number: 200,000 Max Cl/Cd: 53.82 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe505-il-200000-n5.txt Download as CSV file: xf-goe505-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 505 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.0721 0.09328 0.08939 -0.1054 0.9459 0.0350
-10.250 -0.0630 0.08863 0.08472 -0.1097 0.9443 0.0353
-10.000 -0.0651 0.08512 0.08122 -0.1106 0.9366 0.0352
-9.750 -0.0609 0.08013 0.07622 -0.1148 0.9331 0.0354
-9.500 -0.0558 0.07436 0.07043 -0.1205 0.9303 0.0355
-9.250 -0.0664 0.06910 0.06519 -0.1235 0.9218 0.0359
-8.750 -0.2425 0.03619 0.03133 -0.1338 0.8887 0.0352
-8.500 -0.2414 0.03247 0.02710 -0.1325 0.8850 0.0355
-8.250 -0.2442 0.03067 0.02498 -0.1283 0.8783 0.0357
-8.000 -0.2347 0.02884 0.02282 -0.1261 0.8742 0.0360
-7.750 -0.2168 0.02716 0.02078 -0.1252 0.8716 0.0364
-7.500 -0.1941 0.02568 0.01899 -0.1249 0.8697 0.0368
-7.250 -0.1880 0.02497 0.01809 -0.1210 0.8636 0.0371
-7.000 -0.1689 0.02411 0.01700 -0.1196 0.8600 0.0375
-6.750 -0.1456 0.02290 0.01562 -0.1191 0.8575 0.0383
-6.500 -0.1181 0.02189 0.01449 -0.1194 0.8556 0.0389
-6.250 -0.0900 0.02105 0.01354 -0.1196 0.8537 0.0394
-6.000 -0.0826 0.02073 0.01316 -0.1157 0.8474 0.0398
-5.750 -0.0581 0.02009 0.01243 -0.1151 0.8441 0.0403
-5.500 -0.0269 0.01937 0.01161 -0.1157 0.8413 0.0410
-5.250 0.0088 0.01863 0.01075 -0.1172 0.8388 0.0418
-5.000 0.0188 0.01838 0.01045 -0.1136 0.8313 0.0425
-4.750 0.0492 0.01780 0.00978 -0.1140 0.8267 0.0432
-4.500 0.0866 0.01717 0.00903 -0.1157 0.8231 0.0445
-4.000 0.1309 0.01640 0.00817 -0.1131 0.8093 0.0474
-3.750 0.1550 0.01606 0.00777 -0.1122 0.8022 0.0491
-3.500 0.1783 0.01576 0.00741 -0.1111 0.7950 0.0511
-3.000 0.2271 0.01521 0.00683 -0.1094 0.7842 0.0589
-2.750 0.2505 0.01495 0.00660 -0.1084 0.7783 0.0700
-2.500 0.2823 0.01462 0.00627 -0.1091 0.7738 0.0887
-2.250 0.2959 0.01453 0.00624 -0.1061 0.7663 0.1028
-2.000 0.3203 0.01432 0.00609 -0.1053 0.7601 0.1221
-1.750 0.3418 0.01419 0.00600 -0.1039 0.7530 0.1403
-1.500 0.3618 0.01409 0.00593 -0.1022 0.7446 0.1558
-1.250 0.3818 0.01401 0.00586 -0.1004 0.7360 0.1689
-1.000 0.4038 0.01390 0.00574 -0.0991 0.7266 0.1832
-0.750 0.4190 0.01388 0.00569 -0.0963 0.7156 0.1937
-0.500 0.4372 0.01378 0.00559 -0.0942 0.7043 0.2031
-0.250 0.4567 0.01368 0.00548 -0.0923 0.6912 0.2163
0.000 0.4768 0.01359 0.00535 -0.0905 0.6759 0.2303
0.250 0.4980 0.01350 0.00520 -0.0890 0.6577 0.2424
0.500 0.5196 0.01343 0.00505 -0.0875 0.6360 0.2533
0.750 0.5393 0.01344 0.00492 -0.0857 0.6116 0.2637
1.000 0.5559 0.01352 0.00488 -0.0833 0.5862 0.2753
1.250 0.5701 0.01367 0.00491 -0.0805 0.5607 0.2882
1.500 0.5828 0.01387 0.00500 -0.0774 0.5363 0.3036
1.750 0.5950 0.01408 0.00514 -0.0743 0.5134 0.3209
2.000 0.6064 0.01432 0.00529 -0.0711 0.4916 0.3394
2.250 0.6183 0.01456 0.00546 -0.0681 0.4727 0.3603
2.500 0.6300 0.01479 0.00564 -0.0650 0.4554 0.3847
2.750 0.6421 0.01496 0.00582 -0.0621 0.4401 0.4221
3.250 0.8375 0.01556 0.00732 -0.0930 0.3982 1.0000
3.500 0.8487 0.01585 0.00751 -0.0900 0.3908 1.0000
3.750 0.8617 0.01612 0.00771 -0.0872 0.3841 1.0000
4.000 0.8754 0.01640 0.00792 -0.0847 0.3776 1.0000
4.250 0.8883 0.01674 0.00816 -0.0821 0.3711 1.0000
4.500 0.9038 0.01701 0.00840 -0.0799 0.3647 1.0000
4.750 0.9178 0.01735 0.00866 -0.0775 0.3581 1.0000
5.000 0.9333 0.01768 0.00893 -0.0754 0.3526 1.0000
5.250 0.9497 0.01797 0.00920 -0.0735 0.3471 1.0000
5.500 0.9656 0.01832 0.00949 -0.0716 0.3423 1.0000
5.750 0.9817 0.01869 0.00980 -0.0697 0.3380 1.0000
6.000 0.9999 0.01898 0.01010 -0.0682 0.3337 1.0000
6.250 1.0177 0.01930 0.01043 -0.0667 0.3299 1.0000
6.500 1.0348 0.01967 0.01077 -0.0651 0.3260 1.0000
6.750 1.0519 0.02007 0.01112 -0.0635 0.3226 1.0000
7.000 1.0702 0.02041 0.01149 -0.0621 0.3188 1.0000
7.250 1.0885 0.02076 0.01187 -0.0608 0.3152 1.0000
7.500 1.1062 0.02114 0.01226 -0.0594 0.3117 1.0000
7.750 1.1237 0.02155 0.01267 -0.0580 0.3085 1.0000
8.000 1.1415 0.02200 0.01309 -0.0567 0.3055 1.0000
8.250 1.1589 0.02239 0.01355 -0.0553 0.3014 1.0000
8.500 1.1741 0.02284 0.01405 -0.0537 0.2959 1.0000
8.750 1.1862 0.02344 0.01459 -0.0517 0.2894 1.0000
9.000 1.2020 0.02389 0.01514 -0.0502 0.2836 1.0000
9.250 1.2162 0.02444 0.01572 -0.0486 0.2778 1.0000
9.500 1.2287 0.02507 0.01634 -0.0468 0.2715 1.0000
9.750 1.2427 0.02565 0.01699 -0.0453 0.2641 1.0000
10.000 1.2542 0.02638 0.01770 -0.0435 0.2577 1.0000
10.250 1.2690 0.02698 0.01840 -0.0422 0.2502 1.0000
10.500 1.2795 0.02780 0.01922 -0.0404 0.2414 1.0000
10.750 1.2910 0.02862 0.02006 -0.0388 0.2314 1.0000
11.000 1.3004 0.02959 0.02102 -0.0371 0.2184 1.0000
11.250 1.3079 0.03072 0.02212 -0.0353 0.2038 1.0000
11.500 1.3135 0.03202 0.02337 -0.0334 0.1896 1.0000
11.750 1.3134 0.03379 0.02502 -0.0311 0.1709 1.0000
12.000 1.3154 0.03551 0.02667 -0.0291 0.1566 1.0000
12.250 1.3162 0.03738 0.02849 -0.0272 0.1398 1.0000
12.500 1.3015 0.04060 0.03145 -0.0244 0.0939 1.0000
12.750 1.2727 0.04529 0.03589 -0.0213 0.0507 1.0000
13.000 1.2571 0.04911 0.03965 -0.0193 0.0259 1.0000
13.250 1.2531 0.05201 0.04262 -0.0182 0.0221 1.0000
13.500 1.2518 0.05475 0.04546 -0.0174 0.0206 1.0000
13.750 1.2505 0.05757 0.04841 -0.0168 0.0197 1.0000
14.000 1.2484 0.06060 0.05157 -0.0163 0.0189 1.0000
14.250 1.2461 0.06374 0.05485 -0.0161 0.0183 1.0000
14.500 1.2419 0.06724 0.05850 -0.0160 0.0177 1.0000
14.750 1.2366 0.07098 0.06239 -0.0161 0.0173 1.0000
15.000 1.2294 0.07506 0.06662 -0.0164 0.0168 1.0000
15.250 1.2184 0.07979 0.07151 -0.0170 0.0163 1.0000
15.500 1.2091 0.08442 0.07629 -0.0177 0.0162 1.0000
15.750 1.1968 0.08958 0.08161 -0.0187 0.0160 1.0000
16.000 1.1853 0.09471 0.08689 -0.0198 0.0159 1.0000
16.250 1.1713 0.10033 0.09267 -0.0212 0.0157 1.0000
16.500 1.1596 0.10567 0.09815 -0.0226 0.0157 1.0000
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