GOE 476 AIRFOIL (goe476-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 476 AIRFOIL (goe476-il) Reynolds number: 500,000 Max Cl/Cd: 108.4 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe476-il-500000.txt Download as CSV file: xf-goe476-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 476 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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.2110 0.11050 0.10799 -0.0605 0.9906 0.0513
-11.000 -0.5199 0.03707 0.03368 -0.1233 0.9575 0.0498
-10.750 -0.5298 0.03036 0.02632 -0.1262 0.9448 0.0504
-10.500 -0.5010 0.02873 0.02463 -0.1283 0.9383 0.0509
-10.250 -0.4754 0.02760 0.02342 -0.1291 0.9279 0.0514
-10.000 -0.4419 0.02687 0.02264 -0.1309 0.9196 0.0521
-9.750 -0.4193 0.02595 0.02160 -0.1308 0.9055 0.0528
-9.500 -0.4030 0.02442 0.01980 -0.1300 0.8903 0.0534
-9.250 -0.3876 0.02301 0.01810 -0.1286 0.8752 0.0541
-9.000 -0.3712 0.02184 0.01663 -0.1271 0.8612 0.0548
-8.750 -0.3534 0.02092 0.01542 -0.1256 0.8478 0.0553
-8.500 -0.3356 0.02024 0.01449 -0.1239 0.8349 0.0558
-8.250 -0.3174 0.01889 0.01302 -0.1226 0.8233 0.0566
-8.000 -0.2949 0.01844 0.01250 -0.1216 0.8116 0.0573
-7.750 -0.2730 0.01802 0.01200 -0.1205 0.8000 0.0581
-7.500 -0.2505 0.01759 0.01143 -0.1195 0.7895 0.0588
-7.250 -0.2286 0.01709 0.01082 -0.1183 0.7784 0.0596
-7.000 -0.2061 0.01662 0.01019 -0.1172 0.7680 0.0604
-6.750 -0.1836 0.01618 0.00960 -0.1160 0.7567 0.0612
-6.500 -0.1604 0.01585 0.00911 -0.1149 0.7464 0.0619
-6.250 -0.1381 0.01507 0.00822 -0.1139 0.7367 0.0629
-6.000 -0.1140 0.01468 0.00781 -0.1131 0.7284 0.0639
-5.750 -0.0896 0.01442 0.00750 -0.1123 0.7201 0.0650
-5.500 -0.0649 0.01413 0.00713 -0.1115 0.7129 0.0660
-5.250 -0.0400 0.01383 0.00677 -0.1108 0.7055 0.0671
-5.000 -0.0150 0.01359 0.00642 -0.1100 0.6988 0.0682
-4.750 0.0107 0.01341 0.00614 -0.1094 0.6929 0.0690
-4.500 0.0347 0.01282 0.00557 -0.1086 0.6870 0.0707
-4.250 0.0600 0.01262 0.00534 -0.1080 0.6812 0.0721
-4.000 0.0858 0.01246 0.00513 -0.1074 0.6758 0.0737
-3.750 0.1113 0.01226 0.00490 -0.1067 0.6705 0.0752
-3.500 0.1372 0.01212 0.00469 -0.1061 0.6651 0.0765
-3.250 0.1619 0.01178 0.00434 -0.1054 0.6602 0.0786
-3.000 0.1876 0.01163 0.00419 -0.1048 0.6557 0.0808
-2.750 0.2134 0.01149 0.00406 -0.1042 0.6511 0.0834
-2.500 0.2391 0.01135 0.00388 -0.1036 0.6464 0.0858
-2.250 0.2645 0.01118 0.00371 -0.1029 0.6419 0.0892
-2.000 0.2907 0.01110 0.00361 -0.1024 0.6375 0.0928
-1.750 0.3158 0.01094 0.00349 -0.1017 0.6329 0.0974
-1.500 0.3416 0.01086 0.00343 -0.1011 0.6281 0.1035
-1.250 0.3676 0.01079 0.00338 -0.1005 0.6236 0.1115
-1.000 0.3941 0.01077 0.00338 -0.1001 0.6193 0.1217
-0.750 0.4198 0.01071 0.00338 -0.0994 0.6150 0.1329
-0.500 0.4461 0.01073 0.00340 -0.0989 0.6105 0.1431
-0.250 0.4719 0.01069 0.00339 -0.0984 0.6060 0.1530
0.000 0.4992 0.01077 0.00341 -0.0981 0.6015 0.1606
0.250 0.5237 0.01068 0.00340 -0.0973 0.5971 0.1688
0.500 0.5490 0.01067 0.00339 -0.0966 0.5917 0.1754
0.750 0.5739 0.01063 0.00335 -0.0958 0.5862 0.1837
1.000 0.5991 0.01063 0.00336 -0.0952 0.5807 0.1912
1.250 0.6233 0.01057 0.00335 -0.0943 0.5752 0.1993
1.500 0.6480 0.01054 0.00335 -0.0935 0.5700 0.2093
1.750 0.6733 0.01057 0.00336 -0.0928 0.5647 0.2224
2.000 0.6965 0.01047 0.00339 -0.0917 0.5592 0.2428
2.250 0.7188 0.01031 0.00342 -0.0906 0.5534 0.2973
2.500 0.7240 0.00933 0.00351 -0.0861 0.5487 0.6836
2.750 0.9273 0.00938 0.00413 -0.1233 0.5383 1.0000
3.000 0.9489 0.00947 0.00416 -0.1219 0.5323 1.0000
3.250 0.9705 0.00957 0.00422 -0.1206 0.5265 1.0000
3.500 0.9921 0.00964 0.00429 -0.1192 0.5202 1.0000
3.750 1.0131 0.00975 0.00435 -0.1178 0.5143 1.0000
4.000 1.0343 0.00987 0.00444 -0.1163 0.5089 1.0000
4.250 1.0554 0.00995 0.00454 -0.1149 0.5025 1.0000
4.500 1.0754 0.01009 0.00462 -0.1132 0.4965 1.0000
4.750 1.0957 0.01021 0.00473 -0.1116 0.4905 1.0000
5.000 1.1153 0.01033 0.00485 -0.1099 0.4833 1.0000
5.250 1.1328 0.01050 0.00496 -0.1078 0.4753 1.0000
5.500 1.1512 0.01062 0.00508 -0.1058 0.4665 1.0000
5.750 1.1680 0.01083 0.00522 -0.1036 0.4592 1.0000
6.000 1.1872 0.01096 0.00538 -0.1018 0.4529 1.0000
6.250 1.2045 0.01114 0.00554 -0.0996 0.4462 1.0000
6.500 1.2207 0.01134 0.00572 -0.0973 0.4393 1.0000
6.750 1.2371 0.01150 0.00590 -0.0950 0.4315 1.0000
7.000 1.2495 0.01175 0.00609 -0.0919 0.4238 1.0000
7.250 1.2635 0.01189 0.00626 -0.0891 0.4166 1.0000
7.500 1.2735 0.01213 0.00646 -0.0856 0.4085 1.0000
7.750 1.2873 0.01231 0.00667 -0.0828 0.4005 1.0000
8.000 1.2983 0.01259 0.00692 -0.0796 0.3912 1.0000
8.250 1.3121 0.01284 0.00718 -0.0770 0.3809 1.0000
8.500 1.3230 0.01319 0.00750 -0.0740 0.3682 1.0000
8.750 1.3323 0.01362 0.00788 -0.0708 0.3505 1.0000
9.000 1.3378 0.01423 0.00839 -0.0671 0.3257 1.0000
9.250 1.3376 0.01513 0.00913 -0.0627 0.2937 1.0000
9.500 1.3354 0.01626 0.01009 -0.0584 0.2663 1.0000
9.750 1.3381 0.01730 0.01104 -0.0550 0.2497 1.0000
10.000 1.3431 0.01832 0.01201 -0.0521 0.2380 1.0000
10.250 1.3499 0.01932 0.01298 -0.0496 0.2292 1.0000
10.500 1.3584 0.02029 0.01394 -0.0474 0.2217 1.0000
10.750 1.3663 0.02134 0.01498 -0.0453 0.2147 1.0000
11.000 1.3733 0.02250 0.01615 -0.0433 0.2087 1.0000
11.250 1.3855 0.02339 0.01708 -0.0418 0.2035 1.0000
11.500 1.3935 0.02457 0.01827 -0.0401 0.1979 1.0000
11.750 1.4004 0.02589 0.01958 -0.0384 0.1928 1.0000
12.000 1.4129 0.02684 0.02060 -0.0373 0.1878 1.0000
12.250 1.4211 0.02814 0.02191 -0.0358 0.1825 1.0000
12.500 1.4275 0.02961 0.02339 -0.0344 0.1771 1.0000
12.750 1.4387 0.03076 0.02459 -0.0334 0.1721 1.0000
13.000 1.4451 0.03231 0.02615 -0.0322 0.1662 1.0000
13.250 1.4527 0.03380 0.02767 -0.0311 0.1604 1.0000
13.500 1.4597 0.03538 0.02928 -0.0300 0.1539 1.0000
13.750 1.4639 0.03725 0.03115 -0.0290 0.1473 1.0000
14.000 1.4687 0.03911 0.03301 -0.0280 0.1394 1.0000
14.250 1.4716 0.04116 0.03507 -0.0270 0.1318 1.0000
14.500 1.4703 0.04367 0.03756 -0.0261 0.1231 1.0000
14.750 1.4698 0.04615 0.04003 -0.0252 0.1137 1.0000
15.000 1.4680 0.04879 0.04265 -0.0243 0.1046 1.0000
15.250 1.4656 0.05154 0.04539 -0.0236 0.0962 1.0000
15.500 1.4619 0.05449 0.04832 -0.0229 0.0892 1.0000
15.750 1.4600 0.05731 0.05115 -0.0224 0.0839 1.0000
16.000 1.4584 0.06011 0.05397 -0.0219 0.0800 1.0000
16.250 1.4585 0.06281 0.05670 -0.0215 0.0773 1.0000
16.500 1.4556 0.06587 0.05978 -0.0212 0.0745 1.0000
16.750 1.4540 0.06882 0.06277 -0.0210 0.0723 1.0000
17.000 1.4549 0.07152 0.06554 -0.0209 0.0705 1.0000
17.250 1.4550 0.07434 0.06840 -0.0208 0.0688 1.0000
17.500 1.4520 0.07759 0.07168 -0.0209 0.0671 1.0000
17.750 1.4471 0.08109 0.07521 -0.0210 0.0654 1.0000
18.000 1.4482 0.08387 0.07806 -0.0211 0.0644 1.0000
18.250 1.4492 0.08669 0.08096 -0.0213 0.0632 1.0000
18.500 1.4495 0.08963 0.08396 -0.0215 0.0621 1.0000
18.750 1.4488 0.09269 0.08708 -0.0218 0.0612 1.0000
19.000 1.4468 0.09594 0.09038 -0.0223 0.0602 1.0000
19.250 1.4442 0.09924 0.09371 -0.0227 0.0593 1.0000
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