GOE 198 (L.F.G. 5294) AIRFOIL (goe198-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 198 (L.F.G. 5294) AIRFOIL (goe198-il) Reynolds number: 1,000,000 Max Cl/Cd: 116.99 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe198-il-1000000.txt Download as CSV file: xf-goe198-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 198 (L.F.G. 5294) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.2260 0.10510 0.10306 -0.0421 0.8935 0.0166
-9.000 -0.2171 0.10213 0.10010 -0.0438 0.8903 0.0174
-8.750 -0.2096 0.09894 0.09690 -0.0467 0.8862 0.0177
-8.500 -0.1201 0.08148 0.07948 -0.0573 0.8687 0.0179
-8.250 -0.1108 0.07820 0.07618 -0.0569 0.8652 0.0180
-8.000 -0.1027 0.07542 0.07338 -0.0573 0.8612 0.0182
-7.750 -0.1807 0.08642 0.08435 -0.0546 0.8704 0.0180
-7.500 -0.1687 0.08371 0.08162 -0.0557 0.8665 0.0181
-7.250 -0.1554 0.08117 0.07905 -0.0575 0.8619 0.0182
-7.000 -0.1403 0.07853 0.07641 -0.0601 0.8579 0.0184
-6.750 -0.1238 0.07586 0.07373 -0.0631 0.8532 0.0187
-6.500 -0.1060 0.07314 0.07099 -0.0664 0.8489 0.0192
-6.250 -0.0862 0.07023 0.06803 -0.0702 0.8449 0.0198
-6.000 -0.0565 0.06632 0.06410 -0.0781 0.8407 0.0211
-5.750 -0.0239 0.06223 0.05994 -0.0867 0.8363 0.0212
-5.500 0.0048 0.05859 0.05623 -0.0923 0.8322 0.0213
-5.250 0.0329 0.05423 0.05181 -0.0977 0.8285 0.0214
-5.000 0.0516 0.05159 0.04916 -0.0988 0.8247 0.0216
-4.750 0.0758 0.04930 0.04686 -0.1010 0.8206 0.0218
-4.500 0.1026 0.04700 0.04450 -0.1039 0.8165 0.0221
-4.250 0.1319 0.04461 0.04205 -0.1072 0.8122 0.0226
-4.000 0.1634 0.04204 0.03943 -0.1108 0.8068 0.0233
-3.750 0.2101 0.03832 0.03553 -0.1175 0.8014 0.0251
-3.500 0.2468 0.03529 0.03237 -0.1214 0.7962 0.0252
-3.250 0.2819 0.03237 0.02933 -0.1246 0.7905 0.0252
-3.000 0.3116 0.02901 0.02585 -0.1275 0.7847 0.0257
-2.750 0.3408 0.02752 0.02430 -0.1290 0.7788 0.0260
-2.500 0.3711 0.02602 0.02272 -0.1305 0.7716 0.0265
-2.250 0.4029 0.02435 0.02093 -0.1322 0.7639 0.0274
-2.000 0.4445 0.02149 0.01776 -0.1342 0.7550 0.0298
-1.750 0.4780 0.01841 0.01443 -0.1366 0.7457 0.0305
-1.500 0.5074 0.01754 0.01345 -0.1374 0.7342 0.0310
-1.250 0.5373 0.01667 0.01245 -0.1381 0.7205 0.0316
-1.000 0.5678 0.01575 0.01135 -0.1388 0.7042 0.0330
-0.750 0.6004 0.01489 0.01012 -0.1389 0.6822 0.0353
-0.250 0.6656 0.01011 0.00430 -0.1411 0.6207 0.0307
0.000 0.6937 0.00990 0.00385 -0.1411 0.5874 0.0305
0.250 0.7220 0.00970 0.00350 -0.1413 0.5666 0.0305
0.500 0.7506 0.00949 0.00319 -0.1414 0.5518 0.0308
0.750 0.7791 0.00936 0.00301 -0.1416 0.5390 0.0315
1.000 0.8075 0.00928 0.00286 -0.1417 0.5268 0.0319
1.250 0.8361 0.00921 0.00274 -0.1419 0.5152 0.0325
1.500 0.8646 0.00917 0.00266 -0.1420 0.5035 0.0335
1.750 0.8929 0.00918 0.00262 -0.1421 0.4903 0.0344
2.000 0.9210 0.00924 0.00261 -0.1422 0.4753 0.0352
2.250 0.9492 0.00926 0.00257 -0.1423 0.4579 0.0367
2.500 0.9766 0.00941 0.00262 -0.1423 0.4308 0.0390
2.750 1.0024 0.00978 0.00275 -0.1421 0.3798 0.0439
3.000 1.0282 0.01014 0.00300 -0.1418 0.3448 0.0703
3.250 1.0545 0.01042 0.00319 -0.1417 0.3253 0.0823
3.500 1.0810 0.01067 0.00337 -0.1416 0.3082 0.0907
3.750 1.1079 0.01085 0.00351 -0.1415 0.2952 0.0999
4.000 1.1354 0.01087 0.00376 -0.1417 0.2826 0.2608
4.250 1.1570 0.00989 0.00405 -0.1408 0.2696 1.0000
4.500 1.1828 0.01022 0.00423 -0.1405 0.2470 1.0000
4.750 1.2041 0.01108 0.00466 -0.1397 0.1799 1.0000
5.000 1.2186 0.01272 0.00567 -0.1378 0.0688 1.0000
5.250 1.2436 0.01307 0.00596 -0.1374 0.0633 1.0000
5.500 1.2689 0.01337 0.00623 -0.1370 0.0600 1.0000
5.750 1.2943 0.01364 0.00650 -0.1366 0.0585 1.0000
6.000 1.3194 0.01392 0.00680 -0.1362 0.0578 1.0000
6.250 1.3442 0.01422 0.00711 -0.1358 0.0569 1.0000
6.500 1.3685 0.01455 0.00745 -0.1353 0.0558 1.0000
6.750 1.3923 0.01491 0.00783 -0.1347 0.0546 1.0000
7.000 1.4156 0.01531 0.00824 -0.1341 0.0532 1.0000
7.250 1.4384 0.01572 0.00866 -0.1333 0.0520 1.0000
7.500 1.4606 0.01618 0.00914 -0.1325 0.0508 1.0000
7.750 1.4814 0.01671 0.00973 -0.1314 0.0495 1.0000
8.000 1.5030 0.01714 0.01020 -0.1305 0.0490 1.0000
8.250 1.5249 0.01750 0.01058 -0.1296 0.0487 1.0000
8.500 1.5468 0.01783 0.01092 -0.1288 0.0480 1.0000
8.750 1.5678 0.01819 0.01132 -0.1278 0.0472 1.0000
9.000 1.5879 0.01858 0.01174 -0.1267 0.0462 1.0000
9.250 1.6072 0.01901 0.01218 -0.1254 0.0451 1.0000
9.500 1.6257 0.01944 0.01264 -0.1240 0.0441 1.0000
9.750 1.6416 0.01996 0.01318 -0.1222 0.0428 1.0000
10.000 1.6524 0.02071 0.01398 -0.1195 0.0413 1.0000
10.250 1.6700 0.02111 0.01441 -0.1180 0.0400 1.0000
10.500 1.6918 0.02127 0.01457 -0.1173 0.0384 1.0000
10.750 1.7113 0.02158 0.01485 -0.1162 0.0351 1.0000
11.000 1.7283 0.02207 0.01531 -0.1148 0.0298 1.0000
11.250 1.7371 0.02314 0.01623 -0.1124 0.0193 1.0000
11.500 1.7458 0.02428 0.01740 -0.1101 0.0170 1.0000
11.750 1.7536 0.02554 0.01869 -0.1078 0.0156 1.0000
12.000 1.7628 0.02673 0.01996 -0.1057 0.0148 1.0000
12.250 1.7720 0.02796 0.02126 -0.1038 0.0143 1.0000
12.500 1.7794 0.02934 0.02272 -0.1018 0.0137 1.0000
12.750 1.7850 0.03091 0.02435 -0.0997 0.0132 1.0000
13.000 1.7881 0.03275 0.02627 -0.0975 0.0127 1.0000
13.250 1.7874 0.03497 0.02859 -0.0952 0.0121 1.0000
13.500 1.7933 0.03666 0.03036 -0.0936 0.0119 1.0000
13.750 1.7975 0.03856 0.03235 -0.0919 0.0117 1.0000
14.000 1.8000 0.04068 0.03455 -0.0904 0.0115 1.0000
14.250 1.8012 0.04297 0.03694 -0.0888 0.0112 1.0000
14.500 1.8008 0.04551 0.03958 -0.0874 0.0110 1.0000
14.750 1.7996 0.04827 0.04243 -0.0862 0.0108 1.0000
15.000 1.7974 0.05126 0.04552 -0.0852 0.0106 1.0000
15.250 1.7935 0.05457 0.04893 -0.0844 0.0104 1.0000
15.500 1.7875 0.05832 0.05278 -0.0838 0.0102 1.0000
15.750 1.7790 0.06254 0.05712 -0.0835 0.0100 1.0000
16.000 1.7683 0.06722 0.06191 -0.0834 0.0099 1.0000
16.250 1.7538 0.07259 0.06741 -0.0837 0.0098 1.0000
16.500 1.7370 0.07846 0.07343 -0.0843 0.0096 1.0000
16.750 1.7261 0.08352 0.07860 -0.0849 0.0095 1.0000
17.000 1.7185 0.08813 0.08332 -0.0856 0.0095 1.0000
17.250 1.7103 0.09288 0.08818 -0.0864 0.0094 1.0000
17.500 1.7017 0.09775 0.09316 -0.0874 0.0093 1.0000
17.750 1.6923 0.10280 0.09832 -0.0885 0.0092 1.0000
18.000 1.6829 0.10788 0.10350 -0.0898 0.0092 1.0000
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Polar data table (+)
Polar graphs
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