J5012 12% (j5012-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: J5012 12% (j5012-il) Reynolds number: 200,000 Max Cl/Cd: 51.35 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-j5012-il-200000.txt Download as CSV file: xf-j5012-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: J5012 12%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.7689 0.08981 0.08568 -0.0392 1.0000 0.0404
-13.500 -0.7967 0.08110 0.07689 -0.0442 1.0000 0.0400
-13.250 -0.8225 0.07374 0.06942 -0.0482 1.0000 0.0394
-13.000 -0.8523 0.06707 0.06259 -0.0516 1.0000 0.0391
-12.750 -0.8776 0.06180 0.05715 -0.0531 1.0000 0.0387
-12.500 -0.9027 0.05730 0.05244 -0.0530 1.0000 0.0386
-12.250 -0.9249 0.05348 0.04841 -0.0516 1.0000 0.0384
-12.000 -0.9441 0.05032 0.04503 -0.0490 1.0000 0.0383
-11.750 -0.9608 0.04783 0.04231 -0.0454 1.0000 0.0387
-11.500 -0.9764 0.04536 0.03960 -0.0408 1.0000 0.0388
-11.250 -0.9882 0.04320 0.03718 -0.0361 1.0000 0.0392
-11.000 -0.9936 0.04084 0.03453 -0.0322 1.0000 0.0394
-10.750 -0.9944 0.03867 0.03207 -0.0286 1.0000 0.0397
-10.500 -0.9922 0.03679 0.02989 -0.0251 1.0000 0.0401
-10.250 -0.9863 0.03513 0.02794 -0.0219 1.0000 0.0405
-10.000 -0.9749 0.03187 0.02446 -0.0202 1.0000 0.0415
-9.750 -0.9600 0.03031 0.02289 -0.0185 1.0000 0.0429
-9.500 -0.9462 0.02919 0.02169 -0.0165 1.0000 0.0444
-9.250 -0.9318 0.02809 0.02047 -0.0144 1.0000 0.0460
-9.000 -0.9167 0.02693 0.01914 -0.0123 1.0000 0.0477
-8.750 -0.9009 0.02588 0.01791 -0.0101 1.0000 0.0490
-8.500 -0.8832 0.02405 0.01603 -0.0086 1.0000 0.0511
-8.250 -0.8684 0.02310 0.01511 -0.0065 1.0000 0.0537
-8.000 -0.8537 0.02239 0.01434 -0.0042 1.0000 0.0571
-7.750 -0.8391 0.02148 0.01334 -0.0019 1.0000 0.0606
-7.500 -0.8268 0.02050 0.01244 0.0007 1.0000 0.0647
-7.250 -0.8126 0.01987 0.01173 0.0032 1.0000 0.0697
-7.000 -0.8016 0.01894 0.01085 0.0061 1.0000 0.0753
-6.750 -0.7873 0.01845 0.01030 0.0085 1.0000 0.0826
-6.500 -0.7760 0.01768 0.00962 0.0114 1.0000 0.0910
-6.250 -0.7632 0.01706 0.00903 0.0140 1.0000 0.1014
-6.000 -0.7499 0.01648 0.00850 0.0166 1.0000 0.1147
-5.750 -0.7368 0.01590 0.00802 0.0191 1.0000 0.1322
-5.500 -0.7235 0.01532 0.00756 0.0215 1.0000 0.1561
-5.250 -0.7105 0.01473 0.00716 0.0240 1.0000 0.1882
-5.000 -0.6972 0.01418 0.00681 0.0264 1.0000 0.2292
-4.750 -0.6839 0.01367 0.00654 0.0288 1.0000 0.2764
-4.500 -0.6704 0.01322 0.00632 0.0311 1.0000 0.3260
-4.250 -0.6566 0.01283 0.00616 0.0334 1.0000 0.3771
-4.000 -0.6424 0.01251 0.00604 0.0357 1.0000 0.4269
-3.750 -0.6078 0.01231 0.00608 0.0339 0.9948 0.4888
-3.500 -0.5738 0.01212 0.00612 0.0324 0.9888 0.5443
-3.250 -0.5369 0.01205 0.00623 0.0305 0.9834 0.5975
-3.000 -0.5048 0.01192 0.00625 0.0296 0.9763 0.6434
-2.750 -0.4669 0.01188 0.00637 0.0277 0.9710 0.6863
-2.500 -0.4347 0.01182 0.00639 0.0270 0.9636 0.7223
-2.250 -0.3964 0.01181 0.00647 0.0251 0.9580 0.7550
-2.000 -0.3605 0.01181 0.00653 0.0238 0.9518 0.7847
-1.750 -0.3231 0.01182 0.00660 0.0223 0.9452 0.8102
-1.500 -0.2787 0.01185 0.00665 0.0194 0.9412 0.8337
-1.250 -0.2434 0.01190 0.00674 0.0184 0.9334 0.8527
-1.000 -0.1977 0.01196 0.00679 0.0153 0.9287 0.8690
-0.750 -0.1461 0.01200 0.00682 0.0110 0.9259 0.8822
-0.500 -0.1072 0.01207 0.00689 0.0093 0.9179 0.8952
-0.250 -0.0505 0.01214 0.00696 0.0040 0.9142 0.9016
0.000 0.0000 0.01209 0.00689 0.0000 0.9102 0.9101
0.250 0.0506 0.01215 0.00697 -0.0041 0.9016 0.9143
0.500 0.1071 0.01207 0.00689 -0.0093 0.8952 0.9179
0.750 0.1461 0.01200 0.00683 -0.0110 0.8823 0.9259
1.000 0.1977 0.01196 0.00679 -0.0153 0.8690 0.9287
1.250 0.2433 0.01190 0.00673 -0.0184 0.8527 0.9334
1.500 0.2787 0.01184 0.00665 -0.0194 0.8334 0.9412
1.750 0.3231 0.01182 0.00660 -0.0223 0.8103 0.9452
2.000 0.3606 0.01181 0.00653 -0.0238 0.7849 0.9517
2.250 0.3963 0.01181 0.00647 -0.0251 0.7552 0.9580
2.500 0.4347 0.01182 0.00639 -0.0270 0.7223 0.9637
2.750 0.4668 0.01188 0.00637 -0.0277 0.6859 0.9710
3.000 0.5049 0.01192 0.00625 -0.0296 0.6434 0.9764
3.250 0.5370 0.01205 0.00623 -0.0305 0.5976 0.9834
3.500 0.5738 0.01212 0.00612 -0.0324 0.5441 0.9888
3.750 0.6077 0.01230 0.00608 -0.0339 0.4889 0.9948
4.000 0.6424 0.01251 0.00604 -0.0357 0.4268 1.0000
4.250 0.6566 0.01283 0.00616 -0.0334 0.3769 1.0000
4.500 0.6704 0.01321 0.00632 -0.0311 0.3266 1.0000
4.750 0.6839 0.01367 0.00654 -0.0288 0.2764 1.0000
5.000 0.6972 0.01418 0.00681 -0.0264 0.2292 1.0000
5.250 0.7105 0.01473 0.00716 -0.0240 0.1879 1.0000
5.500 0.7234 0.01533 0.00756 -0.0215 0.1558 1.0000
5.750 0.7368 0.01590 0.00801 -0.0191 0.1322 1.0000
6.000 0.7500 0.01647 0.00849 -0.0166 0.1148 1.0000
6.250 0.7632 0.01705 0.00903 -0.0140 0.1015 1.0000
6.500 0.7759 0.01768 0.00962 -0.0114 0.0909 1.0000
6.750 0.7874 0.01843 0.01029 -0.0086 0.0825 1.0000
7.000 0.8016 0.01894 0.01084 -0.0061 0.0751 1.0000
7.250 0.8126 0.01987 0.01173 -0.0032 0.0696 1.0000
7.500 0.8267 0.02051 0.01244 -0.0007 0.0646 1.0000
7.750 0.8390 0.02150 0.01336 0.0019 0.0605 1.0000
8.000 0.8535 0.02234 0.01429 0.0043 0.0567 1.0000
8.250 0.8682 0.02307 0.01508 0.0066 0.0535 1.0000
8.500 0.8833 0.02405 0.01603 0.0086 0.0512 1.0000
8.750 0.9008 0.02587 0.01790 0.0101 0.0490 1.0000
9.000 0.9166 0.02691 0.01913 0.0123 0.0476 1.0000
9.250 0.9319 0.02813 0.02051 0.0144 0.0460 1.0000
9.500 0.9464 0.02932 0.02182 0.0165 0.0444 1.0000
9.750 0.9600 0.03034 0.02290 0.0185 0.0428 1.0000
10.000 0.9750 0.03191 0.02450 0.0202 0.0415 1.0000
10.250 0.9863 0.03514 0.02795 0.0219 0.0405 1.0000
10.500 0.9920 0.03674 0.02984 0.0251 0.0401 1.0000
10.750 0.9945 0.03874 0.03214 0.0285 0.0398 1.0000
11.000 0.9934 0.04095 0.03464 0.0322 0.0395 1.0000
11.250 0.9883 0.04324 0.03722 0.0361 0.0392 1.0000
11.500 0.9772 0.04556 0.03979 0.0406 0.0390 1.0000
11.750 0.9623 0.04772 0.04219 0.0452 0.0387 1.0000
12.000 0.9452 0.05053 0.04522 0.0488 0.0387 1.0000
12.250 0.9249 0.05366 0.04859 0.0515 0.0386 1.0000
12.500 0.9025 0.05738 0.05253 0.0530 0.0386 1.0000
12.750 0.8785 0.06177 0.05711 0.0530 0.0387 1.0000
13.000 0.8530 0.06699 0.06251 0.0514 0.0389 1.0000
13.250 0.8257 0.07345 0.06912 0.0484 0.0394 1.0000
13.500 0.7957 0.08143 0.07723 0.0438 0.0400 1.0000
13.750 0.7761 0.08902 0.08485 0.0405 0.0406 1.0000
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