J5012 12% (j5012-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: J5012 12% (j5012-il) Reynolds number: 100,000 Max Cl/Cd: 38.12 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-j5012-il-100000-n5.txt Download as CSV file: xf-j5012-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.000 -0.8109 0.08511 0.07909 -0.0403 1.0000 0.0329
-13.750 -0.8377 0.07727 0.07109 -0.0452 1.0000 0.0328
-13.500 -0.8635 0.07056 0.06417 -0.0489 1.0000 0.0327
-13.250 -0.8847 0.06514 0.05855 -0.0510 1.0000 0.0327
-13.000 -0.9074 0.06034 0.05348 -0.0522 1.0000 0.0328
-12.750 -0.9245 0.05642 0.04931 -0.0520 1.0000 0.0329
-12.500 -0.9318 0.05351 0.04630 -0.0511 1.0000 0.0334
-12.250 -0.9341 0.05142 0.04415 -0.0500 1.0000 0.0341
-12.000 -0.9398 0.04901 0.04158 -0.0482 1.0000 0.0345
-11.750 -0.9438 0.04688 0.03929 -0.0460 1.0000 0.0350
-11.500 -0.9465 0.04492 0.03717 -0.0435 1.0000 0.0357
-11.250 -0.9482 0.04294 0.03499 -0.0406 1.0000 0.0364
-11.000 -0.9480 0.04106 0.03290 -0.0376 1.0000 0.0372
-10.750 -0.9448 0.03923 0.03085 -0.0347 1.0000 0.0379
-10.500 -0.9385 0.03743 0.02880 -0.0321 1.0000 0.0390
-10.250 -0.9298 0.03581 0.02687 -0.0297 1.0000 0.0403
-10.000 -0.9197 0.03436 0.02540 -0.0276 1.0000 0.0419
-9.750 -0.9092 0.03322 0.02425 -0.0254 1.0000 0.0436
-9.500 -0.8973 0.03202 0.02294 -0.0232 1.0000 0.0455
-9.250 -0.8839 0.03075 0.02151 -0.0211 1.0000 0.0475
-9.000 -0.8697 0.02955 0.02012 -0.0190 1.0000 0.0495
-8.750 -0.8586 0.02837 0.01897 -0.0167 1.0000 0.0517
-8.500 -0.8464 0.02747 0.01803 -0.0144 1.0000 0.0548
-8.250 -0.8328 0.02659 0.01702 -0.0121 1.0000 0.0588
-8.000 -0.8216 0.02561 0.01606 -0.0095 1.0000 0.0624
-7.750 -0.8090 0.02480 0.01522 -0.0071 1.0000 0.0669
-7.500 -0.7964 0.02400 0.01434 -0.0045 1.0000 0.0724
-7.250 -0.7842 0.02323 0.01359 -0.0020 1.0000 0.0786
-7.000 -0.7715 0.02250 0.01284 0.0005 1.0000 0.0861
-6.750 -0.7583 0.02183 0.01215 0.0030 1.0000 0.0951
-6.500 -0.7457 0.02113 0.01150 0.0055 1.0000 0.1055
-6.250 -0.7325 0.02048 0.01088 0.0080 1.0000 0.1183
-6.000 -0.7190 0.01986 0.01031 0.0104 1.0000 0.1340
-5.750 -0.7052 0.01926 0.00979 0.0127 1.0000 0.1539
-5.500 -0.6915 0.01867 0.00931 0.0150 1.0000 0.1782
-5.250 -0.6776 0.01811 0.00889 0.0173 1.0000 0.2081
-5.000 -0.6632 0.01760 0.00851 0.0196 1.0000 0.2418
-4.750 -0.6491 0.01710 0.00819 0.0218 1.0000 0.2803
-4.500 -0.6346 0.01666 0.00792 0.0240 1.0000 0.3215
-4.250 -0.6200 0.01626 0.00770 0.0263 1.0000 0.3660
-4.000 -0.5953 0.01587 0.00753 0.0265 0.9966 0.4192
-3.750 -0.5639 0.01555 0.00742 0.0255 0.9906 0.4750
-3.500 -0.5317 0.01531 0.00738 0.0244 0.9845 0.5281
-3.250 -0.5003 0.01511 0.00733 0.0237 0.9781 0.5758
-3.000 -0.4668 0.01499 0.00733 0.0227 0.9720 0.6200
-2.750 -0.4345 0.01490 0.00733 0.0219 0.9654 0.6600
-2.500 -0.3999 0.01486 0.00737 0.0208 0.9589 0.6961
-2.250 -0.3633 0.01487 0.00742 0.0194 0.9533 0.7284
-2.000 -0.3294 0.01488 0.00746 0.0185 0.9457 0.7563
-1.750 -0.2878 0.01494 0.00752 0.0161 0.9409 0.7817
-1.500 -0.2535 0.01499 0.00759 0.0152 0.9327 0.8037
-1.250 -0.2104 0.01507 0.00765 0.0125 0.9273 0.8229
-1.000 -0.1706 0.01514 0.00771 0.0105 0.9202 0.8398
-0.750 -0.1278 0.01520 0.00776 0.0078 0.9135 0.8545
-0.500 -0.0837 0.01524 0.00778 0.0049 0.9069 0.8672
-0.250 -0.0445 0.01526 0.00779 0.0030 0.8976 0.8797
0.000 0.0000 0.01529 0.00782 0.0000 0.8889 0.8889
0.250 0.0445 0.01526 0.00779 -0.0030 0.8797 0.8976
0.500 0.0836 0.01524 0.00778 -0.0049 0.8672 0.9069
0.750 0.1277 0.01520 0.00776 -0.0078 0.8544 0.9134
1.000 0.1706 0.01514 0.00771 -0.0105 0.8399 0.9203
1.250 0.2104 0.01507 0.00765 -0.0125 0.8229 0.9273
1.500 0.2535 0.01499 0.00759 -0.0152 0.8037 0.9327
1.750 0.2879 0.01494 0.00752 -0.0161 0.7820 0.9409
2.000 0.3294 0.01488 0.00746 -0.0185 0.7563 0.9457
2.250 0.3633 0.01487 0.00742 -0.0194 0.7281 0.9533
2.500 0.3999 0.01486 0.00736 -0.0208 0.6960 0.9590
2.750 0.4345 0.01490 0.00733 -0.0219 0.6604 0.9654
3.000 0.4669 0.01499 0.00733 -0.0227 0.6203 0.9720
3.250 0.5004 0.01511 0.00733 -0.0237 0.5763 0.9781
3.500 0.5317 0.01531 0.00738 -0.0244 0.5282 0.9845
3.750 0.5639 0.01555 0.00742 -0.0255 0.4755 0.9906
4.000 0.5953 0.01587 0.00753 -0.0265 0.4188 0.9966
4.250 0.6199 0.01626 0.00770 -0.0263 0.3657 1.0000
4.500 0.6345 0.01666 0.00792 -0.0240 0.3217 1.0000
4.750 0.6491 0.01710 0.00819 -0.0218 0.2802 1.0000
5.000 0.6632 0.01760 0.00851 -0.0196 0.2420 1.0000
5.250 0.6776 0.01811 0.00888 -0.0173 0.2082 1.0000
5.500 0.6915 0.01867 0.00931 -0.0150 0.1784 1.0000
5.750 0.7052 0.01926 0.00979 -0.0127 0.1542 1.0000
6.000 0.7190 0.01985 0.01031 -0.0104 0.1341 1.0000
6.250 0.7326 0.02047 0.01088 -0.0080 0.1182 1.0000
6.500 0.7458 0.02113 0.01150 -0.0055 0.1052 1.0000
6.750 0.7583 0.02183 0.01215 -0.0030 0.0951 1.0000
7.000 0.7715 0.02250 0.01284 -0.0005 0.0860 1.0000
7.250 0.7842 0.02323 0.01358 0.0020 0.0785 1.0000
7.500 0.7963 0.02400 0.01434 0.0045 0.0723 1.0000
7.750 0.8090 0.02480 0.01522 0.0070 0.0669 1.0000
8.000 0.8215 0.02560 0.01605 0.0095 0.0622 1.0000
8.250 0.8328 0.02659 0.01702 0.0121 0.0587 1.0000
8.500 0.8464 0.02749 0.01805 0.0144 0.0549 1.0000
8.750 0.8586 0.02837 0.01896 0.0167 0.0516 1.0000
9.000 0.8697 0.02956 0.02011 0.0190 0.0494 1.0000
9.250 0.8839 0.03076 0.02152 0.0211 0.0474 1.0000
9.500 0.8970 0.03201 0.02292 0.0233 0.0452 1.0000
9.750 0.9087 0.03318 0.02418 0.0255 0.0433 1.0000
10.000 0.9194 0.03432 0.02536 0.0276 0.0417 1.0000
10.250 0.9298 0.03581 0.02688 0.0297 0.0403 1.0000
10.500 0.9386 0.03742 0.02879 0.0321 0.0390 1.0000
10.750 0.9447 0.03923 0.03085 0.0347 0.0379 1.0000
11.000 0.9477 0.04107 0.03291 0.0376 0.0370 1.0000
11.250 0.9483 0.04295 0.03499 0.0406 0.0364 1.0000
11.500 0.9467 0.04496 0.03720 0.0434 0.0357 1.0000
11.750 0.9438 0.04700 0.03943 0.0460 0.0352 1.0000
12.000 0.9396 0.04913 0.04172 0.0482 0.0346 1.0000
12.250 0.9347 0.05140 0.04413 0.0499 0.0340 1.0000
12.500 0.9311 0.05367 0.04648 0.0511 0.0335 1.0000
12.750 0.9253 0.05648 0.04939 0.0519 0.0330 1.0000
13.000 0.9094 0.06030 0.05342 0.0521 0.0329 1.0000
13.250 0.8885 0.06492 0.05830 0.0512 0.0328 1.0000
13.500 0.8624 0.07080 0.06443 0.0486 0.0327 1.0000
13.750 0.8384 0.07734 0.07116 0.0451 0.0328 1.0000
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