GOE 387 AIRFOIL (goe387-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 387 AIRFOIL (goe387-il) Reynolds number: 1,000,000 Max Cl/Cd: 114.2 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe387-il-1000000-n5.txt Download as CSV file: xf-goe387-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 387 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.3948 0.03333 0.02994 -0.1438 0.7912 0.0194
-11.250 -0.4221 0.03084 0.02722 -0.1395 0.7771 0.0194
-11.000 -0.4313 0.02922 0.02544 -0.1359 0.7658 0.0194
-10.750 -0.4295 0.02783 0.02389 -0.1334 0.7564 0.0195
-10.500 -0.4147 0.02734 0.02334 -0.1319 0.7469 0.0196
-10.250 -0.4053 0.02626 0.02212 -0.1300 0.7383 0.0197
-10.000 -0.3945 0.02515 0.02086 -0.1282 0.7293 0.0197
-9.750 -0.3804 0.02428 0.01986 -0.1266 0.7212 0.0198
-9.500 -0.3648 0.02340 0.01887 -0.1251 0.7138 0.0199
-9.250 -0.3510 0.02227 0.01756 -0.1234 0.7063 0.0200
-9.000 -0.3347 0.02127 0.01641 -0.1219 0.6995 0.0201
-8.750 -0.3164 0.02048 0.01548 -0.1206 0.6922 0.0202
-8.500 -0.2975 0.01974 0.01461 -0.1194 0.6857 0.0204
-8.250 -0.2776 0.01895 0.01370 -0.1182 0.6798 0.0205
-8.000 -0.2574 0.01821 0.01282 -0.1170 0.6734 0.0206
-7.750 -0.2372 0.01742 0.01189 -0.1158 0.6675 0.0207
-7.500 -0.2153 0.01674 0.01110 -0.1149 0.6624 0.0209
-7.250 -0.1931 0.01612 0.01036 -0.1139 0.6563 0.0210
-6.750 -0.1473 0.01501 0.00903 -0.1120 0.6454 0.0213
-6.500 -0.1237 0.01452 0.00845 -0.1112 0.6396 0.0214
-6.250 -0.1001 0.01408 0.00791 -0.1103 0.6340 0.0215
-6.000 -0.0758 0.01364 0.00740 -0.1096 0.6283 0.0217
-5.750 -0.0514 0.01326 0.00694 -0.1088 0.6212 0.0218
-5.500 -0.0274 0.01293 0.00651 -0.1080 0.6137 0.0219
-5.250 -0.0023 0.01258 0.00611 -0.1073 0.6077 0.0220
-5.000 0.0229 0.01229 0.00577 -0.1067 0.6027 0.0221
-4.750 0.0480 0.01205 0.00546 -0.1060 0.5976 0.0222
-4.500 0.0735 0.01178 0.00515 -0.1054 0.5939 0.0223
-4.250 0.0980 0.01136 0.00471 -0.1047 0.5892 0.0226
-4.000 0.1232 0.01109 0.00442 -0.1040 0.5845 0.0228
-3.750 0.1484 0.01091 0.00421 -0.1034 0.5791 0.0231
-3.500 0.1743 0.01071 0.00399 -0.1028 0.5752 0.0232
-3.250 0.2003 0.01052 0.00379 -0.1023 0.5708 0.0234
-3.000 0.2261 0.01036 0.00360 -0.1018 0.5658 0.0237
-2.500 0.2777 0.01007 0.00326 -0.1006 0.5553 0.0242
-2.250 0.3035 0.00994 0.00311 -0.1001 0.5490 0.0245
-2.000 0.3288 0.00984 0.00297 -0.0994 0.5428 0.0248
-1.750 0.3551 0.00972 0.00284 -0.0989 0.5375 0.0250
-1.500 0.3809 0.00963 0.00272 -0.0984 0.5307 0.0253
-1.250 0.4065 0.00957 0.00262 -0.0978 0.5243 0.0256
-1.000 0.4325 0.00950 0.00253 -0.0972 0.5171 0.0258
-0.750 0.4574 0.00945 0.00244 -0.0965 0.5087 0.0261
-0.500 0.4826 0.00936 0.00233 -0.0958 0.4989 0.0266
-0.250 0.5072 0.00935 0.00228 -0.0951 0.4877 0.0271
0.000 0.5312 0.00939 0.00225 -0.0942 0.4731 0.0275
0.250 0.5559 0.00942 0.00224 -0.0934 0.4616 0.0283
0.500 0.5806 0.00945 0.00223 -0.0927 0.4518 0.0290
1.000 0.6292 0.00953 0.00223 -0.0911 0.4310 0.0304
1.250 0.6530 0.00960 0.00226 -0.0902 0.4204 0.0315
1.500 0.6769 0.00967 0.00229 -0.0893 0.4103 0.0328
1.750 0.7007 0.00975 0.00233 -0.0884 0.4003 0.0346
2.000 0.7236 0.00985 0.00239 -0.0874 0.3898 0.0396
2.250 0.7449 0.00966 0.00245 -0.0861 0.3818 0.1475
2.500 0.7649 0.00954 0.00257 -0.0846 0.3736 0.2534
2.750 0.7874 0.00950 0.00266 -0.0835 0.3674 0.3151
3.000 0.8090 0.00948 0.00277 -0.0823 0.3610 0.3757
3.250 0.8221 0.00906 0.00294 -0.0795 0.3559 0.6167
3.750 1.0040 0.00901 0.00362 -0.1075 0.3389 1.0000
4.000 1.0261 0.00913 0.00372 -0.1063 0.3351 1.0000
4.250 1.0475 0.00927 0.00384 -0.1050 0.3301 1.0000
4.500 1.0678 0.00945 0.00398 -0.1035 0.3246 1.0000
4.750 1.0884 0.00962 0.00412 -0.1021 0.3199 1.0000
5.000 1.1097 0.00975 0.00424 -0.1008 0.3164 1.0000
5.250 1.1303 0.00991 0.00438 -0.0993 0.3124 1.0000
5.500 1.1500 0.01010 0.00454 -0.0977 0.3082 1.0000
5.750 1.1693 0.01029 0.00471 -0.0961 0.3044 1.0000
6.000 1.1898 0.01043 0.00486 -0.0947 0.3019 1.0000
6.250 1.2082 0.01058 0.00501 -0.0928 0.2987 1.0000
6.500 1.2241 0.01075 0.00517 -0.0905 0.2947 1.0000
6.750 1.2392 0.01096 0.00536 -0.0880 0.2901 1.0000
7.000 1.2564 0.01114 0.00555 -0.0860 0.2868 1.0000
7.250 1.2742 0.01134 0.00574 -0.0842 0.2815 1.0000
7.500 1.2905 0.01160 0.00597 -0.0821 0.2756 1.0000
7.750 1.3069 0.01189 0.00623 -0.0802 0.2677 1.0000
8.000 1.3225 0.01222 0.00653 -0.0782 0.2593 1.0000
8.250 1.3383 0.01257 0.00685 -0.0762 0.2493 1.0000
8.500 1.3536 0.01297 0.00721 -0.0743 0.2415 1.0000
8.750 1.3680 0.01342 0.00762 -0.0722 0.2302 1.0000
9.000 1.3799 0.01401 0.00814 -0.0699 0.2159 1.0000
9.250 1.3874 0.01483 0.00885 -0.0671 0.1966 1.0000
9.500 1.3984 0.01554 0.00951 -0.0649 0.1861 1.0000
9.750 1.4077 0.01637 0.01028 -0.0626 0.1751 1.0000
10.000 1.4219 0.01700 0.01092 -0.0611 0.1702 1.0000
10.250 1.4367 0.01763 0.01155 -0.0597 0.1668 1.0000
10.500 1.4501 0.01835 0.01228 -0.0582 0.1631 1.0000
10.750 1.4635 0.01910 0.01304 -0.0568 0.1596 1.0000
11.000 1.4785 0.01979 0.01375 -0.0556 0.1574 1.0000
11.250 1.4925 0.02055 0.01454 -0.0544 0.1541 1.0000
11.500 1.5053 0.02142 0.01542 -0.0531 0.1506 1.0000
11.750 1.5170 0.02238 0.01639 -0.0518 0.1476 1.0000
12.000 1.5282 0.02340 0.01743 -0.0505 0.1443 1.0000
12.250 1.5420 0.02426 0.01833 -0.0496 0.1408 1.0000
12.500 1.5546 0.02523 0.01933 -0.0485 0.1384 1.0000
12.750 1.5637 0.02647 0.02057 -0.0473 0.1337 1.0000
13.000 1.5735 0.02769 0.02181 -0.0462 0.1303 1.0000
13.250 1.5839 0.02890 0.02305 -0.0452 0.1258 1.0000
13.500 1.5903 0.03042 0.02457 -0.0441 0.1198 1.0000
13.750 1.5905 0.03250 0.02659 -0.0426 0.1071 1.0000
14.000 1.5816 0.03543 0.02943 -0.0409 0.0902 1.0000
14.250 1.5811 0.03773 0.03172 -0.0397 0.0837 1.0000
14.500 1.5810 0.04007 0.03407 -0.0387 0.0789 1.0000
14.750 1.5841 0.04217 0.03621 -0.0379 0.0754 1.0000
15.000 1.5858 0.04446 0.03853 -0.0372 0.0724 1.0000
15.250 1.5860 0.04692 0.04103 -0.0365 0.0697 1.0000
15.500 1.5894 0.04911 0.04326 -0.0359 0.0675 1.0000
15.750 1.5918 0.05146 0.04566 -0.0355 0.0656 1.0000
16.000 1.5913 0.05413 0.04838 -0.0350 0.0632 1.0000
16.250 1.5910 0.05680 0.05109 -0.0347 0.0614 1.0000
16.500 1.5923 0.05937 0.05372 -0.0344 0.0599 1.0000
16.750 1.5921 0.06215 0.05655 -0.0342 0.0579 1.0000
17.000 1.5918 0.06496 0.05942 -0.0341 0.0564 1.0000
17.250 1.5865 0.06838 0.06287 -0.0340 0.0540 1.0000
17.500 1.5854 0.07138 0.06594 -0.0340 0.0529 1.0000
17.750 1.5850 0.07432 0.06894 -0.0341 0.0516 1.0000
18.000 1.5820 0.07762 0.07230 -0.0343 0.0498 1.0000
18.250 1.5758 0.08135 0.07608 -0.0346 0.0478 1.0000
18.500 1.5707 0.08497 0.07976 -0.0350 0.0462 1.0000
18.750 1.5691 0.08817 0.08303 -0.0354 0.0454 1.0000
19.000 1.5604 0.09236 0.08727 -0.0360 0.0421 1.0000
19.250 1.5540 0.09628 0.09125 -0.0367 0.0407 1.0000
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