GOE 405 AIRFOIL (goe405-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 405 AIRFOIL (goe405-il) Reynolds number: 100,000 Max Cl/Cd: 54.29 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe405-il-100000.txt Download as CSV file: xf-goe405-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 405 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.2641 0.11299 0.10886 -0.0405 0.9794 0.0853
-7.750 -0.2702 0.11280 0.10871 -0.0486 0.9708 0.0874
-7.500 -0.2784 0.11204 0.10799 -0.0566 0.9585 0.0879
-7.250 -0.2381 0.10340 0.09931 -0.0506 0.9599 0.0907
-7.000 -0.2224 0.10020 0.09610 -0.0525 0.9546 0.0942
-6.750 -0.2221 0.09821 0.09413 -0.0541 0.9457 0.0979
-6.500 -0.2269 0.09736 0.09326 -0.0663 0.9317 0.1014
-6.250 -0.2079 0.09182 0.08775 -0.0634 0.9294 0.1038
-6.000 -0.1963 0.08910 0.08501 -0.0622 0.9230 0.1074
-5.750 -0.1820 0.08607 0.08194 -0.0672 0.9151 0.1131
-5.500 -0.1753 0.08311 0.07888 -0.0761 0.9042 0.1167
-5.250 -0.1562 0.07919 0.07499 -0.0738 0.9003 0.1193
-5.000 -0.1437 0.07666 0.07244 -0.0742 0.8929 0.1238
-4.750 -0.1170 0.07263 0.06825 -0.0829 0.8853 0.1323
-4.500 -0.1046 0.07016 0.06579 -0.0809 0.8784 0.1367
-4.250 -0.0711 0.06638 0.06175 -0.0896 0.8708 0.1467
-4.000 -0.0512 0.06331 0.05868 -0.0891 0.8653 0.1503
-3.750 -0.0233 0.06057 0.05566 -0.0941 0.8569 0.1619
-3.500 0.0107 0.05723 0.05230 -0.0960 0.8537 0.1709
-3.250 0.0509 0.04817 0.04207 -0.1050 0.8449 0.1158
-3.000 0.0849 0.04473 0.03859 -0.1071 0.8407 0.1124
-2.750 0.1349 0.03725 0.02982 -0.1122 0.8388 0.1023
-2.500 0.1476 0.03600 0.02832 -0.1102 0.8291 0.1033
-2.250 0.1895 0.03464 0.02682 -0.1125 0.8252 0.1093
-2.000 0.2104 0.03352 0.02524 -0.1113 0.8169 0.1140
-1.750 0.2484 0.03203 0.02349 -0.1128 0.8120 0.1203
-1.500 0.2954 0.03077 0.02205 -0.1154 0.8093 0.1356
-1.250 0.3089 0.03081 0.02201 -0.1131 0.7986 0.1487
-1.000 0.3536 0.02993 0.02109 -0.1153 0.7954 0.1835
-0.750 0.3701 0.03012 0.02121 -0.1134 0.7851 0.2089
-0.500 0.4132 0.02938 0.02048 -0.1155 0.7815 0.2431
-0.250 0.4344 0.02942 0.02043 -0.1144 0.7724 0.2665
0.000 0.4759 0.02841 0.01943 -0.1162 0.7680 0.2880
0.250 0.5283 0.02720 0.01814 -0.1198 0.7658 0.3114
0.500 0.5454 0.02719 0.01818 -0.1179 0.7553 0.3247
0.750 0.5937 0.02598 0.01706 -0.1207 0.7521 0.3505
1.000 0.6454 0.02468 0.01586 -0.1241 0.7497 0.3884
1.250 0.6869 0.02327 0.01596 -0.1269 0.7399 1.0000
1.500 0.7347 0.02261 0.01495 -0.1294 0.7358 1.0000
1.750 0.7545 0.02289 0.01509 -0.1278 0.7250 1.0000
2.000 0.8003 0.02225 0.01424 -0.1301 0.7204 1.0000
2.250 0.8190 0.02256 0.01447 -0.1283 0.7092 1.0000
2.500 0.8656 0.02190 0.01366 -0.1309 0.7044 1.0000
2.750 0.8826 0.02227 0.01398 -0.1288 0.6926 1.0000
3.000 0.9089 0.02234 0.01398 -0.1283 0.6829 1.0000
3.250 0.9460 0.02202 0.01357 -0.1294 0.6754 1.0000
3.500 0.9653 0.02233 0.01386 -0.1277 0.6640 1.0000
3.750 0.9983 0.02218 0.01363 -0.1282 0.6556 1.0000
4.000 1.0257 0.02220 0.01361 -0.1279 0.6458 1.0000
4.250 1.0455 0.02249 0.01390 -0.1263 0.6348 1.0000
4.500 1.0787 0.02235 0.01368 -0.1269 0.6263 1.0000
4.750 1.1027 0.02249 0.01381 -0.1260 0.6159 1.0000
5.000 1.1224 0.02281 0.01418 -0.1245 0.6052 1.0000
5.250 1.1549 0.02275 0.01405 -0.1251 0.5968 1.0000
5.500 1.1761 0.02302 0.01435 -0.1238 0.5864 1.0000
5.750 1.1960 0.02339 0.01477 -0.1224 0.5762 1.0000
6.000 1.2303 0.02334 0.01466 -0.1233 0.5680 1.0000
6.250 1.2464 0.02382 0.01522 -0.1213 0.5572 1.0000
6.500 1.2674 0.02421 0.01566 -0.1201 0.5475 1.0000
6.750 1.3017 0.02422 0.01563 -0.1211 0.5389 1.0000
7.000 1.3143 0.02485 0.01638 -0.1186 0.5282 1.0000
7.250 1.3366 0.02528 0.01687 -0.1177 0.5188 1.0000
7.500 1.3668 0.02550 0.01710 -0.1180 0.5098 1.0000
7.750 1.3796 0.02619 0.01793 -0.1156 0.4994 1.0000
8.000 1.4033 0.02663 0.01842 -0.1149 0.4899 1.0000
8.250 1.4310 0.02672 0.01848 -0.1147 0.4781 1.0000
8.500 1.4505 0.02681 0.01854 -0.1130 0.4637 1.0000
8.750 1.4657 0.02700 0.01876 -0.1106 0.4493 1.0000
9.000 1.4751 0.02738 0.01923 -0.1074 0.4358 1.0000
9.250 1.4835 0.02777 0.01971 -0.1041 0.4224 1.0000
9.500 1.4888 0.02802 0.01998 -0.1002 0.4074 1.0000
9.750 1.4863 0.02832 0.02030 -0.0950 0.3923 1.0000
10.000 1.4824 0.02882 0.02088 -0.0899 0.3780 1.0000
10.250 1.4777 0.02948 0.02163 -0.0850 0.3636 1.0000
10.500 1.4714 0.03033 0.02257 -0.0803 0.3484 1.0000
10.750 1.4625 0.03142 0.02371 -0.0755 0.3308 1.0000
11.000 1.4476 0.03308 0.02542 -0.0707 0.3080 1.0000
11.250 1.4311 0.03527 0.02756 -0.0664 0.2794 1.0000
11.500 1.4121 0.03816 0.03028 -0.0626 0.2436 1.0000
11.750 1.3932 0.04163 0.03352 -0.0595 0.2022 1.0000
12.000 1.3704 0.04588 0.03745 -0.0570 0.1472 1.0000
12.250 1.3427 0.05104 0.04220 -0.0550 0.0951 1.0000
12.500 1.3207 0.05606 0.04703 -0.0536 0.0777 1.0000
12.750 1.3045 0.06078 0.05176 -0.0527 0.0699 1.0000
13.000 1.2901 0.06555 0.05661 -0.0523 0.0656 1.0000
13.250 1.2758 0.07055 0.06171 -0.0522 0.0629 1.0000
13.500 1.2656 0.07521 0.06657 -0.0524 0.0606 1.0000
13.750 1.2544 0.08020 0.07171 -0.0528 0.0584 1.0000
14.000 1.2441 0.08512 0.07678 -0.0534 0.0568 1.0000
14.250 1.2331 0.09021 0.08197 -0.0542 0.0548 1.0000
14.500 1.2251 0.09462 0.08642 -0.0545 0.0530 1.0000
14.750 1.2271 0.09745 0.08933 -0.0543 0.0506 1.0000
15.000 1.2367 0.09889 0.09085 -0.0532 0.0485 1.0000
15.250 1.2570 0.09831 0.09023 -0.0509 0.0463 1.0000
15.500 1.3394 0.08922 0.08060 -0.0425 0.0419 1.0000
15.750 1.3509 0.09125 0.08288 -0.0420 0.0410 1.0000
16.000 1.3709 0.09264 0.08447 -0.0408 0.0402 1.0000
16.250 1.3939 0.09422 0.08627 -0.0396 0.0399 1.0000
16.500 1.4079 0.09693 0.08922 -0.0389 0.0400 1.0000
16.750 1.4130 0.10054 0.09310 -0.0388 0.0402 1.0000
17.000 1.4129 0.10467 0.09750 -0.0390 0.0405 1.0000
17.250 1.4080 0.10925 0.10234 -0.0397 0.0408 1.0000
17.500 1.3999 0.11413 0.10747 -0.0408 0.0410 1.0000
17.750 1.3905 0.11932 0.11289 -0.0422 0.0413 1.0000
18.000 1.3754 0.12494 0.11875 -0.0444 0.0413 1.0000
18.250 1.3647 0.13068 0.12469 -0.0465 0.0416 1.0000
18.500 1.3541 0.13675 0.13095 -0.0488 0.0419 1.0000
18.750 1.3436 0.14222 0.13663 -0.0514 0.0423 1.0000
19.000 1.3223 0.14845 0.14308 -0.0558 0.0427 1.0000
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