GOE 412 AIRFOIL (goe412-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 412 AIRFOIL (goe412-il) Reynolds number: 500,000 Max Cl/Cd: 116.45 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe412-il-500000.txt Download as CSV file: xf-goe412-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 412 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.2023 0.08359 0.08120 -0.0903 0.9725 0.0404
-9.500 -0.1899 0.08182 0.07942 -0.0902 0.9648 0.0408
-9.250 -0.1803 0.08002 0.07762 -0.0899 0.9561 0.0413
-9.000 -0.1758 0.07798 0.07557 -0.0894 0.9441 0.0420
-8.750 -0.1731 0.07538 0.07295 -0.0898 0.9311 0.0428
-8.500 -0.2155 0.05875 0.05625 -0.1106 0.9036 0.0472
-8.250 -0.2811 0.03319 0.02952 -0.1236 0.8830 0.0406
-8.000 -0.2607 0.03199 0.02832 -0.1234 0.8738 0.0412
-7.750 -0.2592 0.02483 0.02036 -0.1228 0.8643 0.0370
-7.500 -0.2448 0.02117 0.01606 -0.1219 0.8553 0.0362
-7.250 -0.2226 0.01955 0.01412 -0.1214 0.8482 0.0362
-7.000 -0.1988 0.01835 0.01268 -0.1210 0.8406 0.0364
-6.500 -0.1482 0.01663 0.01061 -0.1204 0.8276 0.0373
-6.250 -0.1222 0.01590 0.00972 -0.1202 0.8213 0.0379
-6.000 -0.0959 0.01519 0.00886 -0.1200 0.8156 0.0382
-5.750 -0.0694 0.01455 0.00811 -0.1198 0.8096 0.0385
-5.500 -0.0426 0.01401 0.00744 -0.1196 0.8042 0.0388
-5.250 -0.0157 0.01352 0.00686 -0.1194 0.7988 0.0392
-5.000 0.0114 0.01309 0.00635 -0.1193 0.7932 0.0396
-4.750 0.0387 0.01274 0.00591 -0.1191 0.7881 0.0399
-4.500 0.0650 0.01211 0.00523 -0.1189 0.7832 0.0409
-4.250 0.0919 0.01170 0.00481 -0.1188 0.7778 0.0421
-4.000 0.1193 0.01142 0.00449 -0.1187 0.7729 0.0431
-3.750 0.1472 0.01120 0.00420 -0.1187 0.7683 0.0442
-3.500 0.1748 0.01096 0.00395 -0.1186 0.7632 0.0454
-3.250 0.2027 0.01077 0.00371 -0.1186 0.7582 0.0467
-3.000 0.2306 0.01056 0.00347 -0.1186 0.7538 0.0495
-2.750 0.2586 0.01040 0.00332 -0.1186 0.7489 0.0539
-2.500 0.2864 0.01019 0.00320 -0.1186 0.7438 0.0687
-2.250 0.3143 0.01001 0.00309 -0.1186 0.7392 0.0937
-2.000 0.3425 0.00994 0.00304 -0.1187 0.7347 0.1126
-1.750 0.3705 0.00986 0.00301 -0.1187 0.7295 0.1277
-1.500 0.3985 0.00977 0.00294 -0.1187 0.7243 0.1420
-1.250 0.4266 0.00971 0.00286 -0.1188 0.7190 0.1577
-1.000 0.4541 0.00957 0.00280 -0.1187 0.7127 0.1763
-0.750 0.4813 0.00937 0.00274 -0.1187 0.7063 0.2263
-0.500 0.5084 0.00920 0.00274 -0.1186 0.6995 0.2953
-0.250 0.5354 0.00903 0.00271 -0.1185 0.6925 0.3447
0.000 0.5623 0.00884 0.00269 -0.1185 0.6866 0.4164
0.250 0.5862 0.00832 0.00274 -0.1179 0.6797 0.6033
0.500 0.6235 0.00755 0.00288 -0.1193 0.6733 0.9709
0.750 0.6781 0.00760 0.00288 -0.1252 0.6667 1.0000
1.000 0.7036 0.00766 0.00288 -0.1247 0.6603 1.0000
1.250 0.7294 0.00775 0.00288 -0.1243 0.6546 1.0000
1.500 0.7549 0.00780 0.00291 -0.1238 0.6481 1.0000
1.750 0.7804 0.00788 0.00293 -0.1233 0.6420 1.0000
2.000 0.8059 0.00796 0.00298 -0.1228 0.6356 1.0000
2.250 0.8311 0.00804 0.00301 -0.1223 0.6280 1.0000
2.500 0.8564 0.00813 0.00306 -0.1218 0.6206 1.0000
2.750 0.8818 0.00822 0.00312 -0.1213 0.6129 1.0000
3.000 0.9072 0.00833 0.00319 -0.1208 0.6061 1.0000
3.250 0.9326 0.00842 0.00327 -0.1203 0.5979 1.0000
3.500 0.9577 0.00855 0.00335 -0.1198 0.5900 1.0000
3.750 0.9829 0.00866 0.00345 -0.1193 0.5810 1.0000
4.000 1.0077 0.00879 0.00354 -0.1188 0.5717 1.0000
4.250 1.0316 0.00896 0.00365 -0.1180 0.5597 1.0000
4.500 1.0554 0.00911 0.00377 -0.1173 0.5460 1.0000
4.750 1.0790 0.00928 0.00391 -0.1165 0.5323 1.0000
5.000 1.1028 0.00947 0.00406 -0.1158 0.5199 1.0000
5.250 1.1261 0.00968 0.00423 -0.1150 0.5074 1.0000
5.500 1.1487 0.00991 0.00442 -0.1141 0.4938 1.0000
5.750 1.1708 0.01016 0.00463 -0.1131 0.4791 1.0000
6.000 1.1923 0.01044 0.00485 -0.1120 0.4633 1.0000
6.250 1.2131 0.01074 0.00510 -0.1108 0.4461 1.0000
6.500 1.2329 0.01108 0.00538 -0.1094 0.4279 1.0000
6.750 1.2518 0.01146 0.00569 -0.1079 0.4092 1.0000
7.000 1.2693 0.01187 0.00603 -0.1062 0.3905 1.0000
7.500 1.2977 0.01285 0.00684 -0.1015 0.3504 1.0000
7.750 1.3107 0.01342 0.00732 -0.0990 0.3293 1.0000
8.000 1.3235 0.01405 0.00785 -0.0967 0.3094 1.0000
8.250 1.3368 0.01468 0.00841 -0.0945 0.2909 1.0000
8.500 1.3498 0.01536 0.00900 -0.0923 0.2691 1.0000
8.750 1.3606 0.01617 0.00971 -0.0899 0.2466 1.0000
9.000 1.3723 0.01697 0.01042 -0.0877 0.2273 1.0000
9.250 1.3841 0.01780 0.01118 -0.0856 0.2117 1.0000
9.500 1.3960 0.01865 0.01198 -0.0836 0.2001 1.0000
9.750 1.4086 0.01947 0.01279 -0.0818 0.1909 1.0000
10.000 1.4214 0.02032 0.01363 -0.0801 0.1835 1.0000
10.250 1.4341 0.02119 0.01451 -0.0784 0.1768 1.0000
10.500 1.4460 0.02214 0.01547 -0.0768 0.1708 1.0000
10.750 1.4597 0.02300 0.01636 -0.0754 0.1643 1.0000
11.250 1.4845 0.02498 0.01839 -0.0726 0.1507 1.0000
11.500 1.4944 0.02618 0.01958 -0.0710 0.1414 1.0000
11.750 1.5054 0.02733 0.02071 -0.0696 0.1271 1.0000
12.000 1.5019 0.02962 0.02272 -0.0671 0.0891 1.0000
12.250 1.5009 0.03178 0.02483 -0.0649 0.0765 1.0000
12.500 1.5028 0.03377 0.02683 -0.0631 0.0662 1.0000
12.750 1.5003 0.03622 0.02920 -0.0611 0.0484 1.0000
13.000 1.4920 0.03924 0.03206 -0.0589 0.0308 1.0000
13.250 1.4908 0.04177 0.03459 -0.0573 0.0259 1.0000
13.500 1.4935 0.04399 0.03688 -0.0561 0.0239 1.0000
13.750 1.4940 0.04647 0.03942 -0.0549 0.0224 1.0000
14.000 1.4947 0.04901 0.04205 -0.0538 0.0214 1.0000
14.250 1.4970 0.05146 0.04459 -0.0530 0.0206 1.0000
14.500 1.4979 0.05410 0.04732 -0.0522 0.0199 1.0000
14.750 1.4968 0.05701 0.05032 -0.0515 0.0193 1.0000
15.000 1.4930 0.06032 0.05371 -0.0509 0.0187 1.0000
15.250 1.4855 0.06418 0.05766 -0.0504 0.0182 1.0000
15.500 1.4821 0.06764 0.06122 -0.0501 0.0178 1.0000
15.750 1.4804 0.07091 0.06461 -0.0499 0.0174 1.0000
16.000 1.4771 0.07447 0.06827 -0.0498 0.0171 1.0000
16.250 1.4727 0.07824 0.07214 -0.0499 0.0168 1.0000
16.500 1.4674 0.08219 0.07620 -0.0501 0.0165 1.0000
16.750 1.4614 0.08628 0.08038 -0.0505 0.0162 1.0000
17.000 1.4547 0.09053 0.08473 -0.0510 0.0159 1.0000
17.250 1.4472 0.09496 0.08925 -0.0516 0.0157 1.0000
17.500 1.4393 0.09952 0.09389 -0.0524 0.0155 1.0000
17.750 1.4305 0.10422 0.09868 -0.0533 0.0153 1.0000
18.000 1.4213 0.10896 0.10350 -0.0543 0.0151 1.0000
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Polar data table (+)
Polar graphs
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