GOE 384 AIRFOIL (goe384-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 384 AIRFOIL (goe384-il) Reynolds number: 1,000,000 Max Cl/Cd: 105.13 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe384-il-1000000.txt Download as CSV file: xf-goe384-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 384 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
------ -------- --------- --------- -------- -------- --------
-14.250 -0.6754 0.03738 0.03407 -0.1263 0.8215 0.0322
-14.000 -0.6906 0.03329 0.02971 -0.1289 0.8113 0.0324
-13.750 -0.6955 0.03088 0.02710 -0.1286 0.8003 0.0325
-13.500 -0.6962 0.02928 0.02530 -0.1268 0.7879 0.0327
-13.250 -0.6866 0.02797 0.02378 -0.1259 0.7720 0.0328
-13.000 -0.6731 0.02688 0.02249 -0.1250 0.7507 0.0329
-12.750 -0.6644 0.02520 0.02050 -0.1239 0.7222 0.0332
-12.500 -0.6523 0.02369 0.01875 -0.1229 0.6944 0.0335
-12.250 -0.6320 0.02305 0.01799 -0.1224 0.6762 0.0338
-12.000 -0.6094 0.02262 0.01747 -0.1220 0.6645 0.0341
-11.750 -0.5860 0.02220 0.01698 -0.1216 0.6573 0.0344
-11.500 -0.5628 0.02173 0.01643 -0.1213 0.6510 0.0346
-11.250 -0.5396 0.02119 0.01580 -0.1209 0.6461 0.0349
-11.000 -0.5160 0.02062 0.01514 -0.1206 0.6428 0.0352
-10.750 -0.4922 0.02004 0.01447 -0.1202 0.6394 0.0356
-10.500 -0.4681 0.01950 0.01382 -0.1199 0.6356 0.0359
-10.250 -0.4437 0.01898 0.01319 -0.1196 0.6315 0.0363
-10.000 -0.4188 0.01850 0.01259 -0.1193 0.6278 0.0366
-9.750 -0.3930 0.01803 0.01204 -0.1191 0.6258 0.0369
-9.500 -0.3668 0.01764 0.01157 -0.1190 0.6234 0.0371
-9.250 -0.3428 0.01679 0.01062 -0.1187 0.6207 0.0376
-9.000 -0.3175 0.01618 0.00997 -0.1184 0.6182 0.0380
-8.750 -0.2908 0.01586 0.00962 -0.1184 0.6159 0.0384
-8.500 -0.2635 0.01564 0.00936 -0.1183 0.6135 0.0389
-8.250 -0.2362 0.01544 0.00911 -0.1183 0.6104 0.0394
-8.000 -0.2087 0.01518 0.00881 -0.1183 0.6082 0.0399
-7.750 -0.1810 0.01486 0.00845 -0.1183 0.6068 0.0404
-7.500 -0.1532 0.01456 0.00811 -0.1183 0.6052 0.0409
-7.250 -0.1253 0.01429 0.00779 -0.1183 0.6033 0.0413
-7.000 -0.0970 0.01407 0.00752 -0.1184 0.6011 0.0417
-6.750 -0.0706 0.01353 0.00693 -0.1182 0.5988 0.0424
-6.500 -0.0432 0.01320 0.00659 -0.1182 0.5965 0.0430
-6.250 -0.0153 0.01301 0.00638 -0.1183 0.5940 0.0436
-6.000 0.0129 0.01287 0.00620 -0.1183 0.5914 0.0442
-5.750 0.0413 0.01272 0.00603 -0.1185 0.5894 0.0449
-5.500 0.0701 0.01255 0.00584 -0.1186 0.5883 0.0458
-5.250 0.0991 0.01240 0.00567 -0.1188 0.5868 0.0464
-5.000 0.1274 0.01215 0.00540 -0.1189 0.5849 0.0471
-4.750 0.1550 0.01179 0.00505 -0.1189 0.5828 0.0481
-4.500 0.1836 0.01161 0.00488 -0.1191 0.5806 0.0489
-4.250 0.2122 0.01147 0.00473 -0.1193 0.5783 0.0498
-4.000 0.2408 0.01135 0.00458 -0.1194 0.5760 0.0508
-3.750 0.2694 0.01128 0.00447 -0.1195 0.5732 0.0517
-3.500 0.2977 0.01115 0.00431 -0.1197 0.5705 0.0528
-3.250 0.3262 0.01091 0.00410 -0.1198 0.5687 0.0542
-3.000 0.3552 0.01077 0.00398 -0.1201 0.5663 0.0555
-2.750 0.3841 0.01065 0.00386 -0.1203 0.5636 0.0568
-2.500 0.4131 0.01056 0.00375 -0.1205 0.5607 0.0580
-2.250 0.4413 0.01040 0.00358 -0.1207 0.5576 0.0597
-2.000 0.4695 0.01033 0.00350 -0.1208 0.5540 0.0616
-1.750 0.4984 0.01026 0.00343 -0.1210 0.5510 0.0637
-1.500 0.5275 0.01014 0.00333 -0.1213 0.5476 0.0658
-1.250 0.5562 0.01003 0.00324 -0.1215 0.5432 0.0688
-1.000 0.5845 0.00999 0.00318 -0.1217 0.5384 0.0717
-0.750 0.6126 0.00994 0.00314 -0.1218 0.5336 0.0770
-0.500 0.6415 0.00986 0.00311 -0.1221 0.5283 0.0840
-0.250 0.6695 0.00982 0.00308 -0.1222 0.5212 0.0935
0.000 0.6973 0.00980 0.00307 -0.1223 0.5135 0.1036
0.250 0.7243 0.00982 0.00305 -0.1223 0.5018 0.1126
0.500 0.7507 0.00985 0.00306 -0.1221 0.4873 0.1234
0.750 0.7755 0.00991 0.00311 -0.1218 0.4710 0.1476
1.000 0.7989 0.00973 0.00322 -0.1214 0.4571 0.2802
1.250 0.8223 0.00960 0.00338 -0.1209 0.4459 0.4088
1.500 0.8453 0.00941 0.00355 -0.1204 0.4365 0.5606
1.750 0.8674 0.00915 0.00374 -0.1196 0.4295 0.7363
2.000 0.8861 0.00898 0.00397 -0.1177 0.4235 0.8815
2.250 0.9081 0.00914 0.00420 -0.1164 0.4170 0.9559
2.500 0.9506 0.00934 0.00437 -0.1197 0.4122 0.9901
2.750 0.9960 0.00957 0.00454 -0.1238 0.4073 0.9999
3.000 1.0139 0.00976 0.00468 -0.1220 0.4032 1.0000
3.250 1.0314 0.00999 0.00485 -0.1202 0.3987 1.0000
3.500 1.0543 0.01010 0.00495 -0.1195 0.3966 1.0000
3.750 1.0757 0.01024 0.00508 -0.1184 0.3939 1.0000
4.000 1.0955 0.01042 0.00524 -0.1171 0.3909 1.0000
4.250 1.1152 0.01065 0.00544 -0.1158 0.3877 1.0000
4.500 1.1342 0.01094 0.00569 -0.1145 0.3840 1.0000
4.750 1.1549 0.01122 0.00594 -0.1136 0.3809 1.0000
5.000 1.1788 0.01139 0.00612 -0.1132 0.3790 1.0000
5.250 1.2023 0.01159 0.00633 -0.1128 0.3768 1.0000
5.500 1.2249 0.01184 0.00657 -0.1123 0.3744 1.0000
5.750 1.2468 0.01213 0.00684 -0.1116 0.3718 1.0000
6.000 1.2675 0.01247 0.00716 -0.1109 0.3691 1.0000
6.250 1.2868 0.01289 0.00755 -0.1099 0.3659 1.0000
6.500 1.3085 0.01322 0.00788 -0.1093 0.3637 1.0000
6.750 1.3319 0.01347 0.00815 -0.1091 0.3620 1.0000
7.000 1.3547 0.01375 0.00845 -0.1087 0.3600 1.0000
7.250 1.3769 0.01406 0.00877 -0.1083 0.3577 1.0000
7.500 1.3978 0.01445 0.00915 -0.1078 0.3554 1.0000
7.750 1.4176 0.01489 0.00959 -0.1071 0.3531 1.0000
8.000 1.4359 0.01541 0.01010 -0.1062 0.3503 1.0000
8.250 1.4531 0.01599 0.01067 -0.1052 0.3474 1.0000
8.500 1.4753 0.01634 0.01105 -0.1049 0.3462 1.0000
8.750 1.4970 0.01671 0.01146 -0.1046 0.3446 1.0000
9.000 1.5178 0.01714 0.01191 -0.1042 0.3424 1.0000
9.250 1.5373 0.01763 0.01241 -0.1037 0.3392 1.0000
9.500 1.5539 0.01829 0.01305 -0.1028 0.3355 1.0000
9.750 1.5670 0.01915 0.01389 -0.1015 0.3314 1.0000
10.000 1.5878 0.01960 0.01438 -0.1012 0.3297 1.0000
10.250 1.6076 0.02011 0.01494 -0.1008 0.3275 1.0000
10.500 1.6261 0.02071 0.01556 -0.1003 0.3246 1.0000
10.750 1.6426 0.02142 0.01628 -0.0996 0.3216 1.0000
11.000 1.6559 0.02234 0.01720 -0.0986 0.3186 1.0000
11.250 1.6673 0.02338 0.01824 -0.0973 0.3151 1.0000
11.500 1.6860 0.02401 0.01892 -0.0970 0.3131 1.0000
11.750 1.7037 0.02471 0.01967 -0.0966 0.3100 1.0000
12.000 1.7182 0.02563 0.02061 -0.0959 0.3063 1.0000
12.250 1.7288 0.02685 0.02183 -0.0948 0.3027 1.0000
12.500 1.7379 0.02818 0.02317 -0.0937 0.2992 1.0000
12.750 1.7548 0.02899 0.02403 -0.0934 0.2970 1.0000
13.000 1.7697 0.02995 0.02504 -0.0929 0.2936 1.0000
13.250 1.7804 0.03127 0.02638 -0.0921 0.2901 1.0000
13.500 1.7886 0.03279 0.02791 -0.0911 0.2867 1.0000
13.750 1.7969 0.03432 0.02947 -0.0903 0.2833 1.0000
14.000 1.8106 0.03544 0.03065 -0.0898 0.2803 1.0000
14.250 1.8203 0.03692 0.03216 -0.0892 0.2762 1.0000
14.500 1.8235 0.03899 0.03424 -0.0882 0.2713 1.0000
14.750 1.8307 0.04072 0.03600 -0.0874 0.2668 1.0000
15.000 1.8387 0.04237 0.03770 -0.0868 0.2622 1.0000
15.250 1.8406 0.04462 0.03996 -0.0859 0.2572 1.0000
15.500 1.8442 0.04669 0.04205 -0.0851 0.2525 1.0000
15.750 1.8487 0.04873 0.04413 -0.0844 0.2470 1.0000
16.000 1.8446 0.05157 0.04697 -0.0833 0.2407 1.0000
16.250 1.8474 0.05374 0.04918 -0.0826 0.2346 1.0000
16.500 1.8401 0.05694 0.05237 -0.0815 0.2270 1.0000
16.750 1.8384 0.05960 0.05504 -0.0807 0.2192 1.0000
17.000 1.8262 0.06338 0.05882 -0.0796 0.2106 1.0000
17.250 1.8151 0.06706 0.06250 -0.0785 0.2006 1.0000
17.500 1.8028 0.07096 0.06639 -0.0776 0.1910 1.0000
17.750 1.7857 0.07548 0.07091 -0.0767 0.1822 1.0000
18.000 1.7688 0.08004 0.07548 -0.0759 0.1738 1.0000
18.250 1.7560 0.08421 0.07967 -0.0754 0.1664 1.0000
18.500 1.7379 0.08910 0.08458 -0.0749 0.1599 1.0000
18.750 1.7267 0.09328 0.08880 -0.0747 0.1546 1.0000
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Polar data table (+)
Polar graphs
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