GOE 449 AIRFOIL (goe449-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 449 AIRFOIL (goe449-il) Reynolds number: 500,000 Max Cl/Cd: 97.54 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe449-il-500000.txt Download as CSV file: xf-goe449-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 449 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.000 -0.5182 0.04998 0.04666 -0.1414 0.9712 0.0353
-13.750 -0.5412 0.04159 0.03792 -0.1520 0.9642 0.0353
-13.500 -0.5469 0.03682 0.03281 -0.1583 0.9574 0.0355
-13.250 -0.5408 0.03237 0.02809 -0.1633 0.9533 0.0359
-13.000 -0.5258 0.03063 0.02627 -0.1644 0.9448 0.0363
-12.750 -0.5001 0.02912 0.02467 -0.1670 0.9399 0.0369
-12.500 -0.4903 0.02777 0.02317 -0.1663 0.9292 0.0372
-12.250 -0.4730 0.02651 0.02174 -0.1665 0.9217 0.0376
-12.000 -0.4701 0.02558 0.02068 -0.1633 0.9108 0.0379
-11.750 -0.4598 0.02457 0.01949 -0.1614 0.9031 0.0382
-11.500 -0.4515 0.02376 0.01853 -0.1588 0.8947 0.0386
-11.250 -0.4358 0.02282 0.01739 -0.1576 0.8887 0.0391
-11.000 -0.4263 0.02215 0.01659 -0.1548 0.8810 0.0396
-10.750 -0.4112 0.02152 0.01577 -0.1530 0.8745 0.0400
-10.500 -0.3946 0.02078 0.01486 -0.1515 0.8686 0.0404
-10.250 -0.3799 0.01966 0.01369 -0.1497 0.8621 0.0410
-10.000 -0.3600 0.01901 0.01298 -0.1486 0.8567 0.0415
-9.750 -0.3390 0.01849 0.01239 -0.1477 0.8517 0.0421
-9.500 -0.3212 0.01803 0.01189 -0.1460 0.8459 0.0428
-9.250 -0.3007 0.01753 0.01129 -0.1448 0.8407 0.0435
-9.000 -0.2772 0.01705 0.01069 -0.1442 0.8360 0.0442
-8.750 -0.2583 0.01663 0.01020 -0.1426 0.8307 0.0449
-8.500 -0.2368 0.01629 0.00976 -0.1415 0.8258 0.0456
-8.250 -0.2160 0.01557 0.00902 -0.1405 0.8218 0.0467
-8.000 -0.1913 0.01521 0.00862 -0.1400 0.8180 0.0477
-7.750 -0.1710 0.01490 0.00830 -0.1387 0.8136 0.0488
-7.500 -0.1489 0.01456 0.00791 -0.1376 0.8091 0.0499
-7.250 -0.1251 0.01428 0.00754 -0.1368 0.8051 0.0512
-7.000 -0.1018 0.01381 0.00704 -0.1361 0.8015 0.0528
-6.750 -0.0790 0.01356 0.00679 -0.1352 0.7977 0.0544
-6.500 -0.0564 0.01333 0.00655 -0.1342 0.7935 0.0564
-6.250 -0.0331 0.01304 0.00622 -0.1333 0.7894 0.0587
-6.000 -0.0084 0.01278 0.00596 -0.1327 0.7855 0.0617
-5.750 0.0181 0.01265 0.00576 -0.1324 0.7817 0.0651
-5.500 0.0390 0.01235 0.00552 -0.1311 0.7774 0.0689
-5.250 0.0638 0.01223 0.00536 -0.1304 0.7732 0.0731
-5.000 0.0879 0.01196 0.00512 -0.1297 0.7692 0.0781
-4.750 0.1160 0.01189 0.00496 -0.1297 0.7655 0.0830
-4.500 0.1379 0.01167 0.00481 -0.1285 0.7612 0.0886
-4.250 0.1625 0.01158 0.00469 -0.1278 0.7564 0.0931
-4.000 0.1863 0.01134 0.00447 -0.1270 0.7519 0.0990
-3.750 0.2144 0.01127 0.00433 -0.1270 0.7476 0.1043
-3.500 0.2358 0.01107 0.00419 -0.1257 0.7429 0.1103
-3.250 0.2599 0.01095 0.00407 -0.1249 0.7379 0.1165
-3.000 0.2848 0.01078 0.00391 -0.1243 0.7332 0.1241
-2.750 0.3108 0.01070 0.00380 -0.1239 0.7284 0.1323
-2.500 0.3321 0.01052 0.00370 -0.1226 0.7224 0.1445
-2.250 0.3558 0.01035 0.00358 -0.1217 0.7168 0.1612
-2.000 0.3812 0.01020 0.00347 -0.1212 0.7117 0.1862
-1.750 0.4014 0.01000 0.00343 -0.1197 0.7053 0.2200
-1.500 0.4238 0.00981 0.00334 -0.1186 0.6990 0.2615
-1.250 0.4462 0.00962 0.00327 -0.1175 0.6927 0.3096
-1.000 0.4640 0.00932 0.00324 -0.1156 0.6852 0.3809
-0.750 0.4844 0.00905 0.00319 -0.1141 0.6786 0.4783
-0.500 0.4998 0.00875 0.00318 -0.1116 0.6706 0.5544
-0.250 0.5124 0.00837 0.00321 -0.1083 0.6629 0.6961
0.000 0.5284 0.00820 0.00327 -0.1056 0.6545 0.7714
0.250 0.5484 0.00814 0.00336 -0.1036 0.6462 0.8361
0.500 0.5704 0.00820 0.00349 -0.1020 0.6375 0.8829
0.750 0.5946 0.00831 0.00357 -0.1010 0.6287 0.9118
1.000 0.6190 0.00843 0.00367 -0.1001 0.6200 0.9336
1.250 0.6505 0.00861 0.00377 -0.1008 0.6116 0.9501
1.500 0.6925 0.00884 0.00395 -0.1037 0.6030 0.9609
1.750 0.7437 0.00917 0.00418 -0.1086 0.5947 0.9703
2.000 0.7940 0.00945 0.00440 -0.1134 0.5866 0.9771
2.250 0.8381 0.00968 0.00455 -0.1169 0.5789 0.9827
2.500 0.8818 0.00986 0.00467 -0.1205 0.5709 0.9869
2.750 0.9197 0.01006 0.00479 -0.1228 0.5619 0.9921
3.000 0.9640 0.01021 0.00488 -0.1266 0.5541 0.9962
3.250 1.0086 0.01034 0.00497 -0.1304 0.5474 0.9999
3.500 1.0202 0.01049 0.00505 -0.1274 0.5423 1.0000
3.750 1.0294 0.01056 0.00513 -0.1239 0.5377 1.0000
4.000 1.0328 0.01062 0.00519 -0.1191 0.5327 1.0000
4.250 1.0376 0.01071 0.00524 -0.1146 0.5279 1.0000
4.500 1.0473 0.01085 0.00533 -0.1111 0.5232 1.0000
4.750 1.0526 0.01090 0.00541 -0.1067 0.5187 1.0000
5.000 1.0618 0.01101 0.00551 -0.1031 0.5134 1.0000
5.250 1.0761 0.01119 0.00564 -0.1005 0.5085 1.0000
5.500 1.0902 0.01135 0.00580 -0.0980 0.5036 1.0000
5.750 1.1039 0.01149 0.00597 -0.0954 0.4985 1.0000
6.000 1.1190 0.01169 0.00613 -0.0931 0.4931 1.0000
6.250 1.1348 0.01192 0.00633 -0.0910 0.4873 1.0000
6.500 1.1483 0.01211 0.00656 -0.0884 0.4813 1.0000
6.750 1.1637 0.01234 0.00678 -0.0863 0.4755 1.0000
7.000 1.1803 0.01261 0.00702 -0.0844 0.4702 1.0000
7.250 1.1955 0.01284 0.00730 -0.0824 0.4642 1.0000
7.500 1.2098 0.01314 0.00758 -0.0802 0.4574 1.0000
7.750 1.2248 0.01345 0.00791 -0.0782 0.4509 1.0000
8.000 1.2398 0.01377 0.00824 -0.0762 0.4435 1.0000
8.250 1.2536 0.01418 0.00861 -0.0741 0.4369 1.0000
8.500 1.2697 0.01452 0.00901 -0.0725 0.4295 1.0000
8.750 1.2827 0.01499 0.00945 -0.0704 0.4219 1.0000
9.000 1.2979 0.01541 0.00991 -0.0687 0.4136 1.0000
9.250 1.3094 0.01600 0.01046 -0.0666 0.4046 1.0000
9.500 1.3231 0.01653 0.01102 -0.0648 0.3943 1.0000
9.750 1.3341 0.01721 0.01168 -0.0627 0.3843 1.0000
10.000 1.3451 0.01794 0.01238 -0.0608 0.3733 1.0000
10.250 1.3567 0.01867 0.01312 -0.0589 0.3625 1.0000
10.500 1.3660 0.01955 0.01397 -0.0569 0.3517 1.0000
10.750 1.3749 0.02050 0.01488 -0.0549 0.3400 1.0000
11.000 1.3853 0.02141 0.01579 -0.0532 0.3291 1.0000
11.250 1.3934 0.02247 0.01682 -0.0513 0.3182 1.0000
11.500 1.4000 0.02367 0.01799 -0.0493 0.3070 1.0000
11.750 1.4091 0.02476 0.01908 -0.0477 0.2958 1.0000
12.000 1.4159 0.02604 0.02033 -0.0459 0.2851 1.0000
12.250 1.4205 0.02748 0.02173 -0.0440 0.2745 1.0000
12.500 1.4293 0.02871 0.02297 -0.0426 0.2642 1.0000
12.750 1.4346 0.03020 0.02444 -0.0410 0.2553 1.0000
13.000 1.4404 0.03171 0.02594 -0.0395 0.2453 1.0000
13.250 1.4470 0.03318 0.02741 -0.0382 0.2363 1.0000
13.500 1.4497 0.03499 0.02919 -0.0366 0.2273 1.0000
13.750 1.4573 0.03647 0.03070 -0.0355 0.2185 1.0000
14.000 1.4589 0.03846 0.03267 -0.0341 0.2106 1.0000
14.250 1.4657 0.04007 0.03432 -0.0331 0.2019 1.0000
14.500 1.4676 0.04211 0.03634 -0.0318 0.1936 1.0000
14.750 1.4716 0.04405 0.03830 -0.0308 0.1855 1.0000
15.000 1.4738 0.04616 0.04041 -0.0298 0.1774 1.0000
15.250 1.4756 0.04836 0.04263 -0.0289 0.1700 1.0000
15.500 1.4769 0.05065 0.04493 -0.0280 0.1624 1.0000
15.750 1.4772 0.05307 0.04735 -0.0272 0.1558 1.0000
16.000 1.4784 0.05544 0.04974 -0.0265 0.1502 1.0000
16.250 1.4795 0.05787 0.05220 -0.0259 0.1446 1.0000
16.500 1.4770 0.06070 0.05503 -0.0252 0.1399 1.0000
16.750 1.4815 0.06281 0.05721 -0.0248 0.1361 1.0000
17.000 1.4817 0.06541 0.05984 -0.0244 0.1317 1.0000
17.250 1.4784 0.06840 0.06284 -0.0240 0.1275 1.0000
17.500 1.4821 0.07070 0.06521 -0.0238 0.1242 1.0000
17.750 1.4841 0.07317 0.06773 -0.0236 0.1208 1.0000
18.000 1.4813 0.07620 0.07078 -0.0234 0.1169 1.0000
18.250 1.4796 0.07911 0.07373 -0.0233 0.1139 1.0000
18.500 1.4838 0.08140 0.07611 -0.0233 0.1104 1.0000
18.750 1.4827 0.08433 0.07908 -0.0233 0.1069 1.0000
19.000 1.4785 0.08762 0.08239 -0.0234 0.1035 1.0000
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Polar data table (+)
Polar graphs
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