GOE 390 AIRFOIL (goe390-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 390 AIRFOIL (goe390-il) Reynolds number: 1,000,000 Max Cl/Cd: 105.5 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe390-il-1000000.txt Download as CSV file: xf-goe390-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 390 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
------ -------- --------- --------- -------- -------- --------
-16.750 -0.5678 0.07685 0.07401 -0.1128 0.9760 0.0311
-16.500 -0.6083 0.06781 0.06480 -0.1189 0.9659 0.0311
-16.250 -0.6420 0.06042 0.05724 -0.1235 0.9539 0.0312
-16.000 -0.6705 0.05377 0.05044 -0.1276 0.9409 0.0312
-15.750 -0.6952 0.04741 0.04390 -0.1320 0.9256 0.0312
-15.500 -0.7140 0.04145 0.03775 -0.1365 0.9067 0.0313
-15.250 -0.7264 0.03609 0.03217 -0.1413 0.8845 0.0314
-15.000 -0.7315 0.03156 0.02741 -0.1461 0.8643 0.0315
-14.750 -0.7314 0.02823 0.02389 -0.1497 0.8484 0.0316
-14.500 -0.7275 0.02612 0.02161 -0.1510 0.8358 0.0318
-14.250 -0.7197 0.02468 0.02006 -0.1509 0.8260 0.0320
-14.000 -0.7111 0.02367 0.01894 -0.1498 0.8173 0.0321
-13.750 -0.6964 0.02277 0.01798 -0.1491 0.8107 0.0323
-13.500 -0.6794 0.02198 0.01710 -0.1485 0.8038 0.0325
-13.250 -0.6609 0.02127 0.01630 -0.1479 0.7970 0.0327
-13.000 -0.6408 0.02057 0.01554 -0.1474 0.7919 0.0329
-12.750 -0.6200 0.01993 0.01483 -0.1469 0.7858 0.0332
-12.500 -0.5988 0.01935 0.01415 -0.1464 0.7794 0.0334
-12.250 -0.5765 0.01878 0.01351 -0.1459 0.7737 0.0337
-12.000 -0.5534 0.01823 0.01291 -0.1455 0.7678 0.0339
-11.750 -0.5300 0.01775 0.01234 -0.1450 0.7614 0.0342
-11.500 -0.5060 0.01734 0.01184 -0.1446 0.7550 0.0345
-11.250 -0.4809 0.01692 0.01137 -0.1443 0.7498 0.0347
-11.000 -0.4562 0.01650 0.01087 -0.1440 0.7434 0.0349
-10.750 -0.4349 0.01580 0.01009 -0.1432 0.7363 0.0354
-10.500 -0.4107 0.01528 0.00953 -0.1428 0.7297 0.0358
-10.250 -0.3858 0.01488 0.00908 -0.1424 0.7217 0.0362
-10.000 -0.3606 0.01456 0.00869 -0.1420 0.7135 0.0367
-9.750 -0.3344 0.01422 0.00832 -0.1417 0.7065 0.0371
-9.500 -0.3085 0.01394 0.00796 -0.1413 0.6986 0.0376
-9.250 -0.2823 0.01367 0.00763 -0.1410 0.6912 0.0381
-9.000 -0.2556 0.01340 0.00731 -0.1407 0.6842 0.0385
-8.750 -0.2290 0.01319 0.00702 -0.1404 0.6774 0.0389
-8.500 -0.2036 0.01281 0.00659 -0.1400 0.6718 0.0397
-8.250 -0.1768 0.01252 0.00628 -0.1398 0.6667 0.0405
-8.000 -0.1498 0.01230 0.00603 -0.1395 0.6611 0.0414
-7.750 -0.1230 0.01214 0.00580 -0.1392 0.6550 0.0422
-7.500 -0.0952 0.01195 0.00559 -0.1391 0.6506 0.0431
-7.250 -0.0680 0.01169 0.00531 -0.1389 0.6460 0.0444
-7.000 -0.0406 0.01152 0.00512 -0.1387 0.6413 0.0458
-6.750 -0.0132 0.01140 0.00496 -0.1385 0.6365 0.0474
-6.500 0.0144 0.01124 0.00478 -0.1383 0.6323 0.0494
-6.250 0.0428 0.01110 0.00466 -0.1383 0.6287 0.0516
-6.000 0.0709 0.01097 0.00451 -0.1382 0.6243 0.0540
-5.750 0.0988 0.01089 0.00443 -0.1381 0.6197 0.0565
-5.500 0.1264 0.01086 0.00434 -0.1379 0.6147 0.0590
-5.250 0.1550 0.01076 0.00427 -0.1379 0.6115 0.0614
-5.000 0.1840 0.01071 0.00421 -0.1379 0.6080 0.0637
-4.750 0.2119 0.01059 0.00409 -0.1379 0.6040 0.0659
-4.500 0.2399 0.01054 0.00402 -0.1378 0.5998 0.0680
-4.250 0.2676 0.01056 0.00398 -0.1376 0.5947 0.0699
-4.000 0.2957 0.01041 0.00384 -0.1375 0.5912 0.0720
-3.750 0.3241 0.01030 0.00375 -0.1375 0.5871 0.0742
-3.500 0.3521 0.01026 0.00368 -0.1374 0.5825 0.0762
-3.250 0.3794 0.01020 0.00358 -0.1372 0.5777 0.0780
-3.000 0.4066 0.01010 0.00348 -0.1370 0.5731 0.0803
-2.750 0.4351 0.01001 0.00339 -0.1371 0.5691 0.0823
-2.500 0.4631 0.00996 0.00332 -0.1370 0.5640 0.0841
-2.250 0.4898 0.00989 0.00323 -0.1367 0.5582 0.0870
-2.000 0.5170 0.00983 0.00317 -0.1365 0.5527 0.0900
-1.750 0.5450 0.00976 0.00311 -0.1364 0.5470 0.0937
-1.500 0.5717 0.00970 0.00306 -0.1362 0.5405 0.1011
-1.250 0.5980 0.00965 0.00308 -0.1359 0.5340 0.1227
-1.000 0.6257 0.00962 0.00311 -0.1358 0.5271 0.1412
-0.750 0.6515 0.00967 0.00314 -0.1353 0.5186 0.1509
-0.500 0.6785 0.00972 0.00316 -0.1351 0.5104 0.1570
-0.250 0.7039 0.00977 0.00319 -0.1346 0.5008 0.1643
0.000 0.7300 0.00983 0.00323 -0.1343 0.4922 0.1695
0.250 0.7547 0.00993 0.00328 -0.1337 0.4822 0.1748
0.500 0.7800 0.01000 0.00334 -0.1332 0.4736 0.1807
0.750 0.8042 0.01012 0.00341 -0.1325 0.4644 0.1859
1.000 0.8289 0.01020 0.00350 -0.1320 0.4570 0.1950
1.250 0.8536 0.01029 0.00358 -0.1314 0.4499 0.2065
1.500 0.8756 0.01040 0.00372 -0.1304 0.4424 0.2310
1.750 0.9000 0.01037 0.00381 -0.1298 0.4376 0.2764
2.000 0.9227 0.01039 0.00393 -0.1290 0.4323 0.3237
2.250 0.9438 0.01043 0.00410 -0.1279 0.4264 0.3857
2.500 0.9676 0.01037 0.00430 -0.1273 0.4219 0.4911
2.750 0.9927 0.01036 0.00448 -0.1270 0.4177 0.5699
3.000 1.0165 0.01041 0.00467 -0.1264 0.4131 0.6337
3.250 1.0374 0.01030 0.00498 -0.1253 0.4084 0.7961
3.500 1.0652 0.01021 0.00524 -0.1252 0.4044 1.0000
3.750 1.0897 0.01036 0.00538 -0.1247 0.4015 1.0000
4.000 1.1130 0.01055 0.00554 -0.1240 0.3982 1.0000
4.250 1.1354 0.01078 0.00574 -0.1232 0.3947 1.0000
4.500 1.1564 0.01108 0.00598 -0.1222 0.3907 1.0000
4.750 1.1773 0.01138 0.00625 -0.1212 0.3868 1.0000
5.000 1.2021 0.01155 0.00642 -0.1209 0.3847 1.0000
5.250 1.2261 0.01176 0.00663 -0.1205 0.3820 1.0000
5.500 1.2486 0.01202 0.00687 -0.1198 0.3788 1.0000
5.750 1.2697 0.01234 0.00716 -0.1189 0.3754 1.0000
6.000 1.2895 0.01272 0.00751 -0.1179 0.3715 1.0000
6.250 1.3108 0.01306 0.00783 -0.1172 0.3685 1.0000
6.500 1.3345 0.01329 0.00808 -0.1168 0.3663 1.0000
6.750 1.3571 0.01358 0.00837 -0.1163 0.3634 1.0000
7.000 1.3785 0.01392 0.00870 -0.1156 0.3601 1.0000
7.250 1.3979 0.01436 0.00912 -0.1147 0.3567 1.0000
7.500 1.4155 0.01490 0.00963 -0.1135 0.3529 1.0000
7.750 1.4371 0.01526 0.01000 -0.1130 0.3504 1.0000
8.000 1.4591 0.01560 0.01036 -0.1125 0.3477 1.0000
8.250 1.4795 0.01603 0.01080 -0.1119 0.3444 1.0000
8.500 1.4983 0.01655 0.01130 -0.1111 0.3407 1.0000
8.750 1.5142 0.01723 0.01197 -0.1099 0.3368 1.0000
9.000 1.5325 0.01780 0.01254 -0.1091 0.3336 1.0000
9.250 1.5532 0.01825 0.01302 -0.1086 0.3309 1.0000
9.500 1.5720 0.01882 0.01360 -0.1079 0.3274 1.0000
9.750 1.5885 0.01952 0.01429 -0.1070 0.3235 1.0000
10.000 1.6013 0.02046 0.01521 -0.1058 0.3189 1.0000
10.250 1.6197 0.02107 0.01585 -0.1052 0.3157 1.0000
10.500 1.6371 0.02177 0.01656 -0.1045 0.3120 1.0000
10.750 1.6521 0.02261 0.01740 -0.1036 0.3078 1.0000
11.000 1.6630 0.02374 0.01852 -0.1023 0.3031 1.0000
11.250 1.6783 0.02460 0.01940 -0.1015 0.2995 1.0000
11.500 1.6941 0.02543 0.02026 -0.1008 0.2956 1.0000
11.750 1.7057 0.02658 0.02141 -0.0997 0.2910 1.0000
12.000 1.7134 0.02801 0.02282 -0.0984 0.2857 1.0000
12.250 1.7277 0.02899 0.02383 -0.0976 0.2821 1.0000
12.500 1.7396 0.03015 0.02500 -0.0967 0.2774 1.0000
12.750 1.7454 0.03181 0.02665 -0.0954 0.2723 1.0000
13.000 1.7553 0.03316 0.02802 -0.0944 0.2681 1.0000
13.250 1.7660 0.03448 0.02937 -0.0936 0.2641 1.0000
13.500 1.7729 0.03610 0.03100 -0.0925 0.2596 1.0000
13.750 1.7740 0.03825 0.03314 -0.0911 0.2545 1.0000
14.000 1.7863 0.03949 0.03442 -0.0905 0.2515 1.0000
14.250 1.7938 0.04115 0.03611 -0.0896 0.2477 1.0000
14.500 1.7968 0.04320 0.03817 -0.0885 0.2434 1.0000
14.750 1.7973 0.04551 0.04049 -0.0874 0.2391 1.0000
15.000 1.8073 0.04700 0.04203 -0.0868 0.2361 1.0000
15.250 1.8119 0.04899 0.04404 -0.0860 0.2324 1.0000
15.500 1.8119 0.05143 0.04650 -0.0850 0.2284 1.0000
15.750 1.8108 0.05400 0.04908 -0.0840 0.2244 1.0000
16.000 1.8188 0.05571 0.05084 -0.0835 0.2215 1.0000
16.250 1.8219 0.05789 0.05306 -0.0828 0.2180 1.0000
16.500 1.8186 0.06076 0.05594 -0.0819 0.2142 1.0000
16.750 1.8153 0.06364 0.05884 -0.0811 0.2105 1.0000
17.000 1.8217 0.06557 0.06083 -0.0807 0.2081 1.0000
17.250 1.8254 0.06775 0.06305 -0.0803 0.2050 1.0000
17.500 1.8216 0.07078 0.06611 -0.0796 0.2019 1.0000
17.750 1.8162 0.07395 0.06929 -0.0790 0.1984 1.0000
18.000 1.8164 0.07661 0.07201 -0.0787 0.1960 1.0000
18.250 1.8213 0.07874 0.07420 -0.0784 0.1937 1.0000
18.500 1.8214 0.08140 0.07690 -0.0782 0.1912 1.0000
18.750 1.8177 0.08449 0.08003 -0.0779 0.1886 1.0000
19.000 1.8103 0.08805 0.08362 -0.0776 0.1857 1.0000
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