GOE 478 AIRFOIL (goe478-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 478 AIRFOIL (goe478-il) Reynolds number: 500,000 Max Cl/Cd: 101.26 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe478-il-500000.txt Download as CSV file: xf-goe478-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 478 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.2032 0.08510 0.08263 -0.0726 0.9677 0.0451
-9.000 -0.1881 0.08136 0.07888 -0.0767 0.9583 0.0461
-8.750 -0.3608 0.02711 0.02240 -0.1236 0.8976 0.0386
-8.500 -0.3456 0.02529 0.02026 -0.1226 0.8835 0.0385
-8.250 -0.3297 0.02334 0.01802 -0.1215 0.8721 0.0387
-8.000 -0.3131 0.02187 0.01636 -0.1200 0.8614 0.0389
-7.750 -0.2925 0.02073 0.01505 -0.1191 0.8530 0.0391
-7.500 -0.2712 0.01997 0.01422 -0.1182 0.8446 0.0396
-7.250 -0.2480 0.01926 0.01339 -0.1175 0.8381 0.0401
-7.000 -0.2257 0.01855 0.01259 -0.1166 0.8315 0.0405
-6.750 -0.2035 0.01772 0.01159 -0.1156 0.8251 0.0409
-6.500 -0.1797 0.01697 0.01068 -0.1149 0.8197 0.0412
-6.250 -0.1561 0.01629 0.00987 -0.1141 0.8144 0.0416
-6.000 -0.1319 0.01567 0.00915 -0.1133 0.8095 0.0420
-5.750 -0.1069 0.01515 0.00850 -0.1126 0.8048 0.0426
-5.500 -0.0808 0.01471 0.00793 -0.1122 0.8005 0.0430
-5.250 -0.0560 0.01421 0.00735 -0.1115 0.7961 0.0435
-5.000 -0.0320 0.01348 0.00663 -0.1108 0.7913 0.0443
-4.750 -0.0065 0.01309 0.00624 -0.1102 0.7870 0.0452
-4.500 0.0199 0.01280 0.00590 -0.1098 0.7826 0.0462
-4.250 0.0453 0.01250 0.00558 -0.1091 0.7781 0.0473
-4.000 0.0708 0.01222 0.00526 -0.1085 0.7737 0.0482
-3.750 0.0963 0.01187 0.00489 -0.1079 0.7698 0.0492
-3.500 0.1216 0.01149 0.00450 -0.1073 0.7658 0.0506
-3.250 0.1476 0.01126 0.00427 -0.1068 0.7617 0.0521
-3.000 0.1729 0.01104 0.00405 -0.1060 0.7572 0.0539
-2.750 0.1980 0.01075 0.00377 -0.1053 0.7525 0.0562
-2.500 0.2241 0.01055 0.00356 -0.1048 0.7482 0.0594
-2.250 0.2507 0.01037 0.00337 -0.1044 0.7439 0.0639
-2.000 0.2756 0.01015 0.00321 -0.1036 0.7391 0.0709
-1.750 0.3009 0.00994 0.00311 -0.1029 0.7337 0.0889
-1.500 0.3272 0.00980 0.00302 -0.1024 0.7284 0.1139
-1.250 0.3529 0.00967 0.00295 -0.1018 0.7230 0.1322
-1.000 0.3782 0.00955 0.00291 -0.1011 0.7170 0.1505
-0.750 0.4044 0.00946 0.00288 -0.1005 0.7109 0.1726
-0.500 0.4305 0.00940 0.00286 -0.1000 0.7046 0.1943
-0.250 0.4554 0.00929 0.00282 -0.0992 0.6969 0.2142
0.000 0.4813 0.00923 0.00275 -0.0986 0.6892 0.2349
0.250 0.5050 0.00906 0.00271 -0.0976 0.6799 0.2613
0.500 0.5284 0.00883 0.00264 -0.0966 0.6707 0.3245
0.750 0.5440 0.00811 0.00267 -0.0942 0.6588 0.5600
1.000 0.5548 0.00740 0.00273 -0.0902 0.6455 0.8040
1.250 0.6265 0.00738 0.00291 -0.0989 0.6223 0.9576
1.500 0.6692 0.00756 0.00294 -0.1018 0.5952 0.9759
2.000 0.7718 0.00813 0.00310 -0.1117 0.5472 1.0000
2.250 0.7888 0.00835 0.00318 -0.1094 0.5324 1.0000
2.500 0.8073 0.00853 0.00328 -0.1075 0.5197 1.0000
2.750 0.8265 0.00871 0.00338 -0.1056 0.5095 1.0000
3.000 0.8459 0.00889 0.00349 -0.1038 0.5008 1.0000
3.250 0.8660 0.00905 0.00361 -0.1022 0.4934 1.0000
3.500 0.8863 0.00920 0.00372 -0.1006 0.4855 1.0000
3.750 0.9057 0.00941 0.00385 -0.0988 0.4782 1.0000
4.000 0.9271 0.00951 0.00396 -0.0974 0.4716 1.0000
4.250 0.9473 0.00968 0.00409 -0.0957 0.4648 1.0000
4.500 0.9678 0.00986 0.00423 -0.0942 0.4589 1.0000
4.750 0.9892 0.00997 0.00436 -0.0927 0.4527 1.0000
5.000 1.0092 0.01014 0.00449 -0.0911 0.4460 1.0000
5.250 1.0294 0.01030 0.00464 -0.0895 0.4387 1.0000
5.500 1.0495 0.01043 0.00477 -0.0878 0.4309 1.0000
5.750 1.0683 0.01063 0.00493 -0.0860 0.4231 1.0000
6.000 1.0881 0.01076 0.00506 -0.0843 0.4142 1.0000
6.250 1.1059 0.01097 0.00523 -0.0822 0.4058 1.0000
6.500 1.1250 0.01111 0.00539 -0.0804 0.3960 1.0000
6.750 1.1413 0.01132 0.00556 -0.0781 0.3864 1.0000
7.000 1.1568 0.01151 0.00574 -0.0756 0.3761 1.0000
7.250 1.1727 0.01172 0.00593 -0.0732 0.3654 1.0000
7.500 1.1870 0.01199 0.00616 -0.0706 0.3532 1.0000
7.750 1.2009 0.01230 0.00642 -0.0680 0.3380 1.0000
8.000 1.2147 0.01265 0.00671 -0.0654 0.3209 1.0000
8.250 1.2274 0.01308 0.00706 -0.0628 0.3001 1.0000
8.500 1.2379 0.01362 0.00750 -0.0599 0.2778 1.0000
8.750 1.2474 0.01426 0.00802 -0.0569 0.2567 1.0000
9.000 1.2579 0.01491 0.00857 -0.0542 0.2374 1.0000
9.250 1.2685 0.01559 0.00917 -0.0517 0.2206 1.0000
9.500 1.2794 0.01629 0.00980 -0.0492 0.2065 1.0000
9.750 1.2902 0.01703 0.01049 -0.0469 0.1934 1.0000
10.000 1.3016 0.01777 0.01118 -0.0448 0.1815 1.0000
10.250 1.3140 0.01848 0.01187 -0.0428 0.1709 1.0000
10.500 1.3253 0.01930 0.01265 -0.0408 0.1613 1.0000
10.750 1.3356 0.02019 0.01350 -0.0389 0.1518 1.0000
11.000 1.3479 0.02100 0.01432 -0.0372 0.1431 1.0000
11.250 1.3576 0.02200 0.01529 -0.0353 0.1347 1.0000
11.500 1.3672 0.02304 0.01631 -0.0336 0.1261 1.0000
11.750 1.3773 0.02409 0.01736 -0.0320 0.1179 1.0000
12.000 1.3846 0.02537 0.01861 -0.0302 0.1101 1.0000
12.250 1.3922 0.02666 0.01989 -0.0286 0.1029 1.0000
12.500 1.3999 0.02800 0.02124 -0.0271 0.0971 1.0000
12.750 1.4063 0.02946 0.02270 -0.0257 0.0923 1.0000
13.000 1.4122 0.03101 0.02427 -0.0242 0.0883 1.0000
13.250 1.4198 0.03246 0.02576 -0.0230 0.0850 1.0000
13.500 1.4238 0.03424 0.02755 -0.0217 0.0820 1.0000
13.750 1.4273 0.03611 0.02945 -0.0205 0.0795 1.0000
14.000 1.4351 0.03764 0.03106 -0.0195 0.0775 1.0000
14.250 1.4402 0.03947 0.03293 -0.0186 0.0757 1.0000
14.500 1.4436 0.04149 0.03499 -0.0176 0.0741 1.0000
14.750 1.4436 0.04386 0.03739 -0.0167 0.0724 1.0000
15.000 1.4451 0.04616 0.03975 -0.0159 0.0709 1.0000
15.250 1.4506 0.04815 0.04183 -0.0153 0.0697 1.0000
15.500 1.4553 0.05025 0.04400 -0.0149 0.0683 1.0000
15.750 1.4585 0.05254 0.04635 -0.0145 0.0668 1.0000
16.000 1.4589 0.05520 0.04904 -0.0142 0.0654 1.0000
16.250 1.4557 0.05827 0.05214 -0.0139 0.0641 1.0000
16.500 1.4564 0.06097 0.05491 -0.0137 0.0631 1.0000
16.750 1.4606 0.06337 0.05741 -0.0137 0.0623 1.0000
17.000 1.4632 0.06595 0.06007 -0.0138 0.0613 1.0000
17.250 1.4651 0.06864 0.06284 -0.0139 0.0604 1.0000
17.500 1.4662 0.07148 0.06574 -0.0141 0.0593 1.0000
17.750 1.4660 0.07444 0.06876 -0.0143 0.0585 1.0000
18.000 1.4646 0.07750 0.07185 -0.0145 0.0575 1.0000
18.250 1.4624 0.08048 0.07484 -0.0145 0.0564 1.0000
18.500 1.4641 0.08335 0.07782 -0.0150 0.0557 1.0000
18.750 1.4648 0.08640 0.08098 -0.0157 0.0549 1.0000
19.000 1.4654 0.08937 0.08404 -0.0162 0.0541 1.0000
19.250 1.4651 0.09250 0.08724 -0.0168 0.0532 1.0000
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