GOE 515 AIRFOIL (goe515-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 515 AIRFOIL (goe515-il) Reynolds number: 50,000 Max Cl/Cd: 37.93 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe515-il-50000-n5.txt Download as CSV file: xf-goe515-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 515 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.4555 0.12058 0.11302 -0.0278 1.0000 0.0697
-10.500 -0.4535 0.11670 0.10917 -0.0291 1.0000 0.0697
-10.250 -0.4535 0.11277 0.10530 -0.0307 1.0000 0.0698
-10.000 -0.4509 0.10884 0.10140 -0.0317 1.0000 0.0697
-9.750 -0.4471 0.10500 0.09759 -0.0323 1.0000 0.0692
-9.500 -0.4460 0.10116 0.09380 -0.0332 1.0000 0.0689
-9.250 -0.4481 0.09731 0.09000 -0.0347 1.0000 0.0690
-9.000 -0.4431 0.09464 0.08736 -0.0343 1.0000 0.0724
-8.750 -0.4427 0.09154 0.08432 -0.0347 1.0000 0.0738
-8.500 -0.4465 0.08822 0.08107 -0.0355 1.0000 0.0748
-8.250 -0.4547 0.08472 0.07768 -0.0363 1.0000 0.0748
-8.000 -0.4630 0.08076 0.07381 -0.0377 1.0000 0.0745
-7.750 -0.4699 0.07656 0.06967 -0.0392 1.0000 0.0742
-7.500 -0.4759 0.07219 0.06533 -0.0405 1.0000 0.0740
-7.250 -0.4804 0.06791 0.06103 -0.0414 1.0000 0.0742
-7.000 -0.4823 0.06406 0.05714 -0.0417 1.0000 0.0757
-6.750 -0.4838 0.06003 0.05299 -0.0419 1.0000 0.0780
-6.500 -0.4853 0.05533 0.04805 -0.0422 1.0000 0.0799
-6.250 -0.4853 0.05028 0.04260 -0.0421 1.0000 0.0813
-6.000 -0.4812 0.04562 0.03743 -0.0415 1.0000 0.0823
-5.750 -0.4712 0.04285 0.03444 -0.0402 1.0000 0.0838
-5.500 -0.4584 0.04093 0.03236 -0.0387 1.0000 0.0859
-5.250 -0.4448 0.03905 0.03023 -0.0374 1.0000 0.0896
-5.000 -0.4305 0.03622 0.02674 -0.0364 1.0000 0.0953
-4.750 -0.4144 0.03428 0.02453 -0.0352 1.0000 0.0987
-4.500 -0.3968 0.03272 0.02275 -0.0340 1.0000 0.1020
-4.250 -0.3779 0.03099 0.02060 -0.0329 1.0000 0.1065
-4.000 -0.3575 0.02922 0.01830 -0.0319 1.0000 0.1121
-3.750 -0.3388 0.02855 0.01763 -0.0309 1.0000 0.1196
-3.500 -0.3183 0.02761 0.01641 -0.0299 1.0000 0.1289
-3.250 -0.2974 0.02682 0.01543 -0.0290 1.0000 0.1376
-3.000 -0.2670 0.02624 0.01472 -0.0300 0.9957 0.1507
-2.750 -0.2334 0.02569 0.01402 -0.0316 0.9899 0.1647
-2.500 -0.1985 0.02527 0.01345 -0.0334 0.9843 0.1799
-2.250 -0.1648 0.02484 0.01289 -0.0348 0.9781 0.1933
-2.000 -0.1290 0.02451 0.01245 -0.0367 0.9725 0.2077
-1.750 -0.0941 0.02417 0.01199 -0.0383 0.9662 0.2207
-1.500 -0.0588 0.02392 0.01170 -0.0401 0.9604 0.2386
-1.250 -0.0259 0.02363 0.01141 -0.0413 0.9533 0.2567
-1.000 0.0100 0.02332 0.01119 -0.0433 0.9474 0.2826
-0.750 0.0398 0.02293 0.01104 -0.0441 0.9395 0.3244
-0.500 0.1048 0.02068 0.01101 -0.0511 0.9393 1.0000
-0.250 0.1415 0.02096 0.01094 -0.0531 0.9317 1.0000
0.000 0.1746 0.02120 0.01094 -0.0543 0.9224 1.0000
0.250 0.2071 0.02144 0.01099 -0.0554 0.9126 1.0000
0.500 0.2486 0.02162 0.01102 -0.0581 0.9046 1.0000
0.750 0.2797 0.02179 0.01109 -0.0588 0.8928 1.0000
1.000 0.3132 0.02194 0.01115 -0.0599 0.8814 1.0000
1.250 0.3498 0.02203 0.01120 -0.0614 0.8709 1.0000
1.500 0.3889 0.02206 0.01120 -0.0632 0.8614 1.0000
1.750 0.4180 0.02218 0.01132 -0.0633 0.8489 1.0000
2.000 0.4472 0.02231 0.01146 -0.0633 0.8367 1.0000
2.250 0.4771 0.02242 0.01160 -0.0634 0.8248 1.0000
2.500 0.5087 0.02248 0.01171 -0.0637 0.8134 1.0000
2.750 0.5428 0.02247 0.01178 -0.0643 0.8027 1.0000
3.000 0.5691 0.02260 0.01199 -0.0637 0.7890 1.0000
3.250 0.5957 0.02272 0.01220 -0.0630 0.7750 1.0000
3.500 0.6224 0.02282 0.01242 -0.0623 0.7607 1.0000
3.750 0.6492 0.02290 0.01262 -0.0615 0.7458 1.0000
4.000 0.6763 0.02295 0.01280 -0.0608 0.7304 1.0000
4.250 0.7052 0.02282 0.01282 -0.0599 0.7131 1.0000
4.500 0.7273 0.02276 0.01287 -0.0579 0.6889 1.0000
4.750 0.7524 0.02246 0.01265 -0.0560 0.6608 1.0000
5.000 0.7767 0.02223 0.01249 -0.0540 0.6294 1.0000
5.250 0.8003 0.02222 0.01254 -0.0522 0.5991 1.0000
5.500 0.8229 0.02236 0.01276 -0.0504 0.5692 1.0000
5.750 0.8450 0.02255 0.01300 -0.0486 0.5363 1.0000
6.000 0.8647 0.02288 0.01339 -0.0465 0.4996 1.0000
6.250 0.8830 0.02328 0.01372 -0.0441 0.4565 1.0000
6.500 0.8977 0.02392 0.01415 -0.0414 0.4055 1.0000
6.750 0.9090 0.02482 0.01481 -0.0384 0.3496 1.0000
7.000 0.9193 0.02588 0.01566 -0.0356 0.2962 1.0000
7.250 0.9293 0.02708 0.01665 -0.0330 0.2466 1.0000
7.500 0.9386 0.02845 0.01782 -0.0304 0.2059 1.0000
7.750 0.9480 0.03000 0.01914 -0.0280 0.1748 1.0000
8.000 0.9581 0.03170 0.02069 -0.0258 0.1490 1.0000
8.250 0.9678 0.03345 0.02231 -0.0237 0.1265 1.0000
8.500 0.9796 0.03506 0.02398 -0.0217 0.1061 1.0000
8.750 0.9907 0.03669 0.02567 -0.0197 0.0902 1.0000
9.000 1.0021 0.03834 0.02738 -0.0177 0.0782 1.0000
9.250 1.0149 0.04015 0.02924 -0.0160 0.0700 1.0000
9.500 1.0307 0.04209 0.03135 -0.0145 0.0625 1.0000
9.750 1.0453 0.04424 0.03360 -0.0131 0.0567 1.0000
10.000 1.0639 0.04677 0.03645 -0.0120 0.0524 1.0000
10.250 1.0764 0.04914 0.03897 -0.0106 0.0493 1.0000
10.500 1.0870 0.05193 0.04182 -0.0093 0.0465 1.0000
10.750 1.0892 0.05490 0.04528 -0.0070 0.0446 1.0000
11.000 1.0879 0.05805 0.04880 -0.0049 0.0431 1.0000
11.250 1.0828 0.06145 0.05252 -0.0030 0.0421 1.0000
11.500 1.0740 0.06513 0.05650 -0.0015 0.0415 1.0000
11.750 1.0613 0.06916 0.06082 -0.0005 0.0412 1.0000
12.000 1.0451 0.07366 0.06559 -0.0003 0.0411 1.0000
12.250 1.0251 0.07888 0.07105 -0.0011 0.0410 1.0000
12.500 1.0019 0.08502 0.07742 -0.0032 0.0413 1.0000
12.750 0.9754 0.09243 0.08502 -0.0070 0.0418 1.0000
13.000 0.9467 0.10146 0.09419 -0.0125 0.0425 1.0000
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Polar data table (+)
Polar graphs
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