GOE 405 AIRFOIL (goe405-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 405 AIRFOIL (goe405-il) Reynolds number: 100,000 Max Cl/Cd: 58.07 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe405-il-100000-n5.txt Download as CSV file: xf-goe405-il-100000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.1071 0.09350 0.08875 -0.0856 0.9403 0.0376
-8.250 -0.0918 0.08961 0.08484 -0.0886 0.9357 0.0372
-8.000 -0.0866 0.08589 0.08114 -0.0920 0.9268 0.0375
-7.250 -0.0620 0.07356 0.06880 -0.1040 0.9018 0.0379
-7.000 -0.0506 0.06921 0.06439 -0.1080 0.8942 0.0379
-6.750 -0.0425 0.06495 0.06008 -0.1114 0.8851 0.0379
-6.500 -0.0253 0.06311 0.05823 -0.1123 0.8795 0.0400
-6.250 -0.0067 0.06056 0.05561 -0.1147 0.8736 0.0421
-6.000 0.0050 0.05678 0.05175 -0.1175 0.8647 0.0432
-5.750 0.0224 0.05170 0.04650 -0.1221 0.8580 0.0435
-5.500 0.0375 0.04678 0.04135 -0.1252 0.8498 0.0448
-5.250 0.0608 0.03709 0.03096 -0.1319 0.8450 0.0477
-5.000 0.0711 0.03175 0.02481 -0.1320 0.8357 0.0488
-4.750 0.0996 0.02959 0.02236 -0.1332 0.8320 0.0513
-4.500 0.1208 0.02857 0.02114 -0.1326 0.8254 0.0542
-4.250 0.1460 0.02656 0.01864 -0.1327 0.8198 0.0563
-4.000 0.1784 0.02468 0.01626 -0.1337 0.8163 0.0588
-3.750 0.2002 0.02370 0.01494 -0.1326 0.8088 0.0619
-3.500 0.2300 0.02282 0.01398 -0.1330 0.8033 0.0652
-3.250 0.2614 0.02188 0.01281 -0.1335 0.7982 0.0683
-3.000 0.2852 0.02122 0.01196 -0.1326 0.7903 0.0717
-2.750 0.3187 0.02040 0.01100 -0.1334 0.7859 0.0768
-2.500 0.3410 0.02012 0.01066 -0.1324 0.7781 0.0845
-2.250 0.3715 0.01966 0.01017 -0.1327 0.7728 0.0975
-2.000 0.3996 0.01931 0.00977 -0.1326 0.7670 0.1157
-1.750 0.4253 0.01919 0.00963 -0.1321 0.7601 0.1349
-1.500 0.4589 0.01902 0.00937 -0.1330 0.7556 0.1562
-1.250 0.4804 0.01921 0.00950 -0.1318 0.7475 0.1758
-1.000 0.5113 0.01918 0.00940 -0.1323 0.7420 0.1974
-0.750 0.5359 0.01913 0.00926 -0.1316 0.7348 0.2101
-0.500 0.5639 0.01895 0.00904 -0.1316 0.7283 0.2214
-0.250 0.5920 0.01876 0.00881 -0.1315 0.7220 0.2312
0.000 0.6172 0.01867 0.00868 -0.1310 0.7144 0.2421
0.250 0.6478 0.01848 0.00841 -0.1313 0.7086 0.2549
0.500 0.6699 0.01847 0.00842 -0.1302 0.7000 0.2654
0.750 0.7022 0.01826 0.00815 -0.1309 0.6942 0.2808
1.000 0.7224 0.01831 0.00824 -0.1295 0.6850 0.2959
1.250 0.7536 0.01810 0.00802 -0.1301 0.6787 0.3189
1.500 0.7735 0.01807 0.00815 -0.1287 0.6691 0.3543
1.750 0.8206 0.01679 0.00808 -0.1325 0.6621 1.0000
2.000 0.8417 0.01700 0.00819 -0.1312 0.6526 1.0000
2.250 0.8663 0.01713 0.00821 -0.1305 0.6441 1.0000
2.500 0.8903 0.01728 0.00826 -0.1297 0.6351 1.0000
2.750 0.9120 0.01747 0.00839 -0.1285 0.6255 1.0000
3.000 0.9388 0.01756 0.00837 -0.1282 0.6171 1.0000
3.250 0.9584 0.01781 0.00859 -0.1267 0.6064 1.0000
3.500 0.9810 0.01799 0.00872 -0.1257 0.5967 1.0000
3.750 1.0059 0.01813 0.00877 -0.1251 0.5874 1.0000
4.000 1.0255 0.01839 0.00904 -0.1237 0.5763 1.0000
4.250 1.0472 0.01861 0.00922 -0.1225 0.5659 1.0000
4.500 1.0711 0.01879 0.00932 -0.1218 0.5562 1.0000
4.750 1.0905 0.01908 0.00962 -0.1203 0.5450 1.0000
5.000 1.1109 0.01936 0.00989 -0.1190 0.5345 1.0000
5.250 1.1332 0.01961 0.01009 -0.1181 0.5248 1.0000
5.500 1.1528 0.01994 0.01043 -0.1167 0.5145 1.0000
5.750 1.1726 0.02028 0.01078 -0.1153 0.5047 1.0000
6.000 1.1950 0.02058 0.01103 -0.1145 0.4961 1.0000
6.250 1.2126 0.02099 0.01150 -0.1128 0.4863 1.0000
6.500 1.2329 0.02136 0.01189 -0.1116 0.4778 1.0000
6.750 1.2513 0.02176 0.01232 -0.1101 0.4689 1.0000
7.000 1.2696 0.02220 0.01279 -0.1086 0.4606 1.0000
7.250 1.2889 0.02262 0.01324 -0.1073 0.4525 1.0000
7.500 1.3057 0.02312 0.01383 -0.1056 0.4442 1.0000
7.750 1.3252 0.02357 0.01431 -0.1044 0.4364 1.0000
8.000 1.3404 0.02413 0.01497 -0.1025 0.4282 1.0000
8.250 1.3599 0.02461 0.01549 -0.1014 0.4209 1.0000
8.500 1.3734 0.02523 0.01624 -0.0993 0.4124 1.0000
8.750 1.3847 0.02581 0.01687 -0.0968 0.4011 1.0000
9.000 1.3910 0.02648 0.01755 -0.0937 0.3876 1.0000
9.250 1.3955 0.02725 0.01836 -0.0904 0.3737 1.0000
9.500 1.4000 0.02814 0.01935 -0.0874 0.3607 1.0000
9.750 1.4043 0.02910 0.02039 -0.0845 0.3474 1.0000
10.000 1.4068 0.03020 0.02156 -0.0815 0.3328 1.0000
10.250 1.4086 0.03144 0.02285 -0.0787 0.3175 1.0000
10.500 1.4071 0.03294 0.02435 -0.0757 0.2993 1.0000
10.750 1.4014 0.03485 0.02626 -0.0727 0.2748 1.0000
11.000 1.3938 0.03712 0.02843 -0.0698 0.2483 1.0000
11.250 1.3848 0.03974 0.03094 -0.0672 0.2205 1.0000
11.500 1.3727 0.04287 0.03392 -0.0648 0.1866 1.0000
11.750 1.3501 0.04724 0.03794 -0.0625 0.1311 1.0000
12.000 1.3256 0.05221 0.04256 -0.0606 0.0774 1.0000
12.250 1.3036 0.05729 0.04746 -0.0592 0.0538 1.0000
12.500 1.2916 0.06155 0.05175 -0.0584 0.0432 1.0000
12.750 1.2831 0.06559 0.05590 -0.0580 0.0371 1.0000
13.000 1.2745 0.06982 0.06023 -0.0578 0.0336 1.0000
13.250 1.2671 0.07407 0.06465 -0.0579 0.0311 1.0000
13.500 1.2591 0.07856 0.06930 -0.0582 0.0297 1.0000
13.750 1.2496 0.08340 0.07430 -0.0588 0.0286 1.0000
14.000 1.2384 0.08868 0.07973 -0.0597 0.0277 1.0000
14.250 1.2283 0.09394 0.08515 -0.0608 0.0270 1.0000
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Polar data table (+)
Polar graphs
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