GOE 414 AIRFOIL (goe414-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 414 AIRFOIL (goe414-il) Reynolds number: 100,000 Max Cl/Cd: 52.08 at α=9.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe414-il-100000.txt Download as CSV file: xf-goe414-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 414 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3591 0.11806 0.11390 -0.0309 1.0000 0.1055
-8.750 -0.3857 0.11766 0.11363 -0.0302 1.0000 0.1062
-8.500 -0.4128 0.11717 0.11325 -0.0289 1.0000 0.1065
-8.250 -0.4332 0.11512 0.11128 -0.0344 0.9950 0.1068
-8.000 -0.3743 0.10796 0.10402 -0.0278 0.9966 0.1117
-7.750 -0.3599 0.10406 0.10010 -0.0323 0.9906 0.1161
-7.500 -0.3748 0.10068 0.09677 -0.0448 0.9775 0.1209
-7.250 -0.3574 0.09449 0.09058 -0.0502 0.9713 0.1230
-7.000 -0.3313 0.09148 0.08752 -0.0478 0.9662 0.1271
-6.750 -0.3323 0.08513 0.08095 -0.0693 0.9479 0.1367
-6.500 -0.3010 0.08186 0.07782 -0.0614 0.9458 0.1404
-6.000 -0.2751 0.05553 0.05048 -0.0887 0.9271 0.0939
-5.750 -0.2560 0.05071 0.04539 -0.0902 0.9171 0.0896
-5.500 -0.2202 0.04377 0.03765 -0.0958 0.9121 0.0897
-5.250 -0.1976 0.03964 0.03289 -0.0966 0.9022 0.0900
-5.000 -0.1560 0.03578 0.02825 -0.1002 0.8977 0.0942
-4.750 -0.1313 0.03458 0.02699 -0.1002 0.8884 0.0987
-4.500 -0.0902 0.03235 0.02414 -0.1026 0.8838 0.1048
-4.250 -0.0617 0.03114 0.02279 -0.1031 0.8762 0.1128
-4.000 -0.0245 0.02961 0.02095 -0.1047 0.8704 0.1244
-3.750 0.0213 0.02828 0.01952 -0.1078 0.8672 0.1479
-3.500 0.0426 0.02779 0.01887 -0.1067 0.8569 0.1675
-3.250 0.0873 0.02680 0.01797 -0.1097 0.8533 0.1890
-3.000 0.1099 0.02667 0.01783 -0.1090 0.8435 0.2064
-2.750 0.1524 0.02607 0.01713 -0.1114 0.8393 0.2295
-2.500 0.1802 0.02569 0.01675 -0.1113 0.8310 0.2451
-2.250 0.2174 0.02486 0.01596 -0.1125 0.8253 0.2627
-2.000 0.2605 0.02383 0.01500 -0.1146 0.8221 0.2929
-1.750 0.2817 0.02351 0.01486 -0.1133 0.8112 0.3290
-1.500 0.3213 0.02229 0.01396 -0.1148 0.8075 0.4103
-1.250 0.3424 0.02177 0.01381 -0.1134 0.7968 0.4930
-1.000 0.4186 0.01973 0.01303 -0.1208 0.7945 1.0000
-0.750 0.4447 0.01972 0.01276 -0.1203 0.7849 1.0000
-0.500 0.4817 0.01932 0.01210 -0.1214 0.7784 1.0000
-0.250 0.5051 0.01936 0.01196 -0.1203 0.7673 1.0000
0.000 0.5450 0.01885 0.01123 -0.1218 0.7617 1.0000
0.250 0.5671 0.01893 0.01117 -0.1206 0.7495 1.0000
0.500 0.5928 0.01892 0.01103 -0.1199 0.7385 1.0000
0.750 0.6301 0.01855 0.01046 -0.1211 0.7316 1.0000
1.000 0.6528 0.01870 0.01051 -0.1200 0.7193 1.0000
1.250 0.6778 0.01882 0.01052 -0.1193 0.7081 1.0000
1.500 0.7091 0.01875 0.01031 -0.1196 0.6994 1.0000
1.750 0.7362 0.01885 0.01030 -0.1193 0.6889 1.0000
2.000 0.7600 0.01911 0.01048 -0.1186 0.6779 1.0000
2.250 0.7905 0.01918 0.01042 -0.1189 0.6698 1.0000
2.500 0.8146 0.01952 0.01071 -0.1183 0.6600 1.0000
2.750 0.8392 0.01990 0.01104 -0.1178 0.6514 1.0000
3.000 0.8669 0.02018 0.01124 -0.1178 0.6439 1.0000
3.250 0.8895 0.02069 0.01173 -0.1171 0.6359 1.0000
3.500 0.9167 0.02100 0.01200 -0.1170 0.6289 1.0000
3.750 0.9399 0.02154 0.01254 -0.1164 0.6220 1.0000
4.000 0.9633 0.02206 0.01307 -0.1159 0.6153 1.0000
4.250 0.9940 0.02231 0.01326 -0.1164 0.6100 1.0000
4.500 1.0101 0.02304 0.01408 -0.1148 0.6015 1.0000
4.750 1.0428 0.02313 0.01409 -0.1154 0.5958 1.0000
5.000 1.0573 0.02387 0.01497 -0.1135 0.5871 1.0000
5.250 1.0893 0.02393 0.01495 -0.1141 0.5809 1.0000
5.500 1.1042 0.02473 0.01589 -0.1123 0.5733 1.0000
5.750 1.1301 0.02515 0.01634 -0.1121 0.5679 1.0000
6.000 1.1566 0.02561 0.01685 -0.1120 0.5631 1.0000
6.250 1.1702 0.02654 0.01794 -0.1102 0.5562 1.0000
6.500 1.1998 0.02679 0.01822 -0.1105 0.5513 1.0000
6.750 1.2160 0.02766 0.01926 -0.1090 0.5452 1.0000
7.000 1.2357 0.02834 0.02005 -0.1079 0.5391 1.0000
7.250 1.2699 0.02846 0.02019 -0.1089 0.5348 1.0000
7.500 1.2747 0.02979 0.02176 -0.1058 0.5273 1.0000
7.750 1.3146 0.02899 0.02092 -0.1070 0.5186 1.0000
8.000 1.3413 0.02833 0.02024 -0.1061 0.5051 1.0000
8.250 1.3576 0.02832 0.02033 -0.1039 0.4925 1.0000
8.500 1.3772 0.02814 0.02021 -0.1021 0.4795 1.0000
8.750 1.3970 0.02800 0.02013 -0.1003 0.4664 1.0000
9.000 1.4151 0.02763 0.01973 -0.0981 0.4495 1.0000
9.250 1.4294 0.02768 0.01983 -0.0956 0.4350 1.0000
9.500 1.4395 0.02764 0.01979 -0.0923 0.4173 1.0000
9.750 1.4437 0.02775 0.01989 -0.0881 0.3988 1.0000
10.000 1.4352 0.02829 0.02055 -0.0822 0.3820 1.0000
10.250 1.4257 0.02916 0.02158 -0.0767 0.3636 1.0000
10.500 1.4161 0.03031 0.02284 -0.0719 0.3406 1.0000
10.750 1.4038 0.03201 0.02457 -0.0674 0.3055 1.0000
11.000 1.3865 0.03443 0.02669 -0.0630 0.2591 1.0000
11.250 1.3661 0.03774 0.02969 -0.0592 0.2214 1.0000
11.500 1.3454 0.04160 0.03335 -0.0562 0.1761 1.0000
11.750 1.3172 0.04654 0.03796 -0.0537 0.1241 1.0000
12.000 1.2922 0.05165 0.04288 -0.0519 0.0998 1.0000
12.250 1.2721 0.05664 0.04780 -0.0508 0.0807 1.0000
12.500 1.2560 0.06144 0.05260 -0.0501 0.0698 1.0000
12.750 1.2432 0.06607 0.05728 -0.0498 0.0637 1.0000
13.000 1.2305 0.07084 0.06210 -0.0497 0.0599 1.0000
13.250 1.2190 0.07560 0.06693 -0.0497 0.0571 1.0000
13.500 1.2104 0.08008 0.07155 -0.0499 0.0545 1.0000
13.750 1.2020 0.08458 0.07617 -0.0502 0.0524 1.0000
14.000 1.1937 0.08907 0.08074 -0.0505 0.0507 1.0000
14.250 1.1868 0.09329 0.08503 -0.0507 0.0493 1.0000
14.500 1.1856 0.09642 0.08820 -0.0504 0.0481 1.0000
14.750 1.1922 0.09832 0.09021 -0.0495 0.0468 1.0000
15.000 1.2047 0.09901 0.09094 -0.0479 0.0454 1.0000
15.250 1.2223 0.09876 0.09068 -0.0457 0.0438 1.0000
15.500 1.2431 0.09805 0.08988 -0.0431 0.0418 1.0000
15.750 1.2964 0.09273 0.08427 -0.0366 0.0394 1.0000
16.000 1.3221 0.09298 0.08469 -0.0344 0.0391 1.0000
16.250 1.3465 0.09393 0.08582 -0.0325 0.0390 1.0000
16.500 1.3652 0.09595 0.08806 -0.0312 0.0391 1.0000
16.750 1.3766 0.09896 0.09130 -0.0304 0.0392 1.0000
17.000 1.3785 0.10275 0.09534 -0.0303 0.0393 1.0000
17.250 1.3747 0.10702 0.09986 -0.0306 0.0394 1.0000
17.500 1.3678 0.11166 0.10474 -0.0314 0.0394 1.0000
17.750 1.3590 0.11660 0.10992 -0.0325 0.0395 1.0000
18.000 1.3469 0.12160 0.11518 -0.0342 0.0397 1.0000
18.250 1.3307 0.12689 0.12072 -0.0368 0.0399 1.0000
18.500 1.3107 0.13301 0.12712 -0.0403 0.0402 1.0000
18.750 1.2815 0.14144 0.13590 -0.0457 0.0411 1.0000
19.000 1.2153 0.15895 0.15396 -0.0583 0.0435 1.0000
19.250 1.1752 0.17345 0.16869 -0.0683 0.0453 1.0000
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