J5012 12% (j5012-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: J5012 12% (j5012-il) Reynolds number: 100,000 Max Cl/Cd: 41.4 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-j5012-il-100000.txt Download as CSV file: xf-j5012-il-100000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.8513 0.06820 0.06220 -0.0471 1.0000 0.0715
-11.250 -0.8787 0.06620 0.06000 -0.0429 1.0000 0.0711
-11.000 -0.8927 0.06231 0.05595 -0.0400 1.0000 0.0708
-10.750 -0.9066 0.05891 0.05234 -0.0367 1.0000 0.0707
-10.500 -0.9185 0.05554 0.04871 -0.0332 1.0000 0.0707
-10.250 -0.9255 0.05210 0.04499 -0.0298 1.0000 0.0705
-10.000 -0.9307 0.04887 0.04143 -0.0262 1.0000 0.0706
-9.750 -0.9332 0.04596 0.03815 -0.0225 1.0000 0.0708
-9.500 -0.9320 0.04309 0.03492 -0.0190 1.0000 0.0712
-9.250 -0.9232 0.03962 0.03125 -0.0169 1.0000 0.0724
-9.000 -0.9094 0.03769 0.02930 -0.0152 1.0000 0.0751
-8.750 -0.8967 0.03597 0.02740 -0.0129 1.0000 0.0780
-8.500 -0.8851 0.03405 0.02514 -0.0103 1.0000 0.0807
-8.250 -0.8728 0.03235 0.02301 -0.0074 1.0000 0.0832
-8.000 -0.8519 0.03001 0.02075 -0.0066 1.0000 0.0875
-7.750 -0.8355 0.02877 0.01938 -0.0046 1.0000 0.0933
-7.500 -0.8167 0.02715 0.01767 -0.0030 1.0000 0.0997
-7.250 -0.7993 0.02600 0.01647 -0.0012 1.0000 0.1077
-7.000 -0.7816 0.02471 0.01526 0.0005 1.0000 0.1172
-6.750 -0.7649 0.02356 0.01412 0.0025 1.0000 0.1287
-6.500 -0.7495 0.02251 0.01315 0.0047 1.0000 0.1427
-6.250 -0.7352 0.02153 0.01226 0.0070 1.0000 0.1598
-6.000 -0.7215 0.02060 0.01140 0.0096 1.0000 0.1825
-5.750 -0.7098 0.01961 0.01064 0.0123 1.0000 0.2115
-5.500 -0.6996 0.01861 0.00999 0.0154 1.0000 0.2491
-5.250 -0.6899 0.01772 0.00943 0.0185 1.0000 0.3001
-5.000 -0.6802 0.01695 0.00901 0.0217 1.0000 0.3582
-4.750 -0.6695 0.01636 0.00873 0.0249 1.0000 0.4185
-4.500 -0.6576 0.01590 0.00854 0.0280 1.0000 0.4764
-4.250 -0.6446 0.01557 0.00843 0.0310 1.0000 0.5309
-4.000 -0.6307 0.01534 0.00836 0.0340 1.0000 0.5821
-3.750 -0.6157 0.01519 0.00837 0.0368 1.0000 0.6291
-3.500 -0.5996 0.01512 0.00846 0.0396 1.0000 0.6725
-3.250 -0.5825 0.01514 0.00859 0.0422 1.0000 0.7133
-3.000 -0.5652 0.01522 0.00874 0.0448 1.0000 0.7518
-2.750 -0.5457 0.01540 0.00895 0.0472 1.0000 0.7872
-2.500 -0.5233 0.01569 0.00927 0.0490 1.0000 0.8205
-2.250 -0.4965 0.01611 0.00968 0.0500 1.0000 0.8517
-2.000 -0.4638 0.01665 0.01016 0.0497 1.0000 0.8800
-1.750 -0.4147 0.01741 0.01083 0.0463 1.0000 0.9014
-1.500 -0.3596 0.01817 0.01147 0.0415 1.0000 0.9193
-1.250 -0.2956 0.01887 0.01206 0.0346 1.0000 0.9329
-1.000 -0.2364 0.01940 0.01249 0.0283 1.0000 0.9469
-0.750 -0.1790 0.01979 0.01281 0.0220 1.0000 0.9610
-0.500 -0.1213 0.02007 0.01304 0.0153 1.0000 0.9746
-0.250 -0.0623 0.02024 0.01319 0.0081 1.0000 0.9876
0.000 0.0000 0.02036 0.01329 0.0000 1.0000 1.0000
0.250 0.0622 0.02024 0.01318 -0.0081 0.9876 1.0000
0.500 0.1212 0.02007 0.01304 -0.0153 0.9746 1.0000
0.750 0.1790 0.01979 0.01281 -0.0220 0.9610 1.0000
1.000 0.2359 0.01940 0.01249 -0.0282 0.9470 1.0000
1.250 0.2953 0.01888 0.01206 -0.0346 0.9330 1.0000
1.500 0.3595 0.01817 0.01147 -0.0415 0.9194 1.0000
1.750 0.4146 0.01741 0.01083 -0.0463 0.9014 1.0000
2.000 0.4639 0.01664 0.01015 -0.0498 0.8799 1.0000
2.250 0.4965 0.01610 0.00968 -0.0500 0.8516 1.0000
2.500 0.5233 0.01569 0.00927 -0.0490 0.8206 1.0000
2.750 0.5457 0.01540 0.00896 -0.0472 0.7876 1.0000
3.000 0.5652 0.01522 0.00872 -0.0449 0.7520 1.0000
3.250 0.5824 0.01514 0.00859 -0.0422 0.7132 1.0000
3.500 0.5996 0.01512 0.00845 -0.0396 0.6727 1.0000
3.750 0.6157 0.01519 0.00837 -0.0368 0.6293 1.0000
4.000 0.6306 0.01533 0.00837 -0.0340 0.5819 1.0000
4.250 0.6446 0.01557 0.00843 -0.0310 0.5308 1.0000
4.500 0.6576 0.01590 0.00853 -0.0280 0.4767 1.0000
4.750 0.6695 0.01635 0.00872 -0.0249 0.4185 1.0000
5.000 0.6802 0.01695 0.00901 -0.0217 0.3581 1.0000
5.250 0.6899 0.01773 0.00943 -0.0185 0.3001 1.0000
5.500 0.6996 0.01862 0.00999 -0.0154 0.2490 1.0000
5.750 0.7098 0.01961 0.01064 -0.0123 0.2118 1.0000
6.000 0.7216 0.02059 0.01140 -0.0096 0.1827 1.0000
6.250 0.7352 0.02152 0.01225 -0.0070 0.1598 1.0000
6.500 0.7494 0.02251 0.01314 -0.0047 0.1425 1.0000
6.750 0.7649 0.02354 0.01411 -0.0025 0.1287 1.0000
7.000 0.7815 0.02470 0.01525 -0.0005 0.1171 1.0000
7.250 0.7992 0.02600 0.01647 0.0012 0.1076 1.0000
7.500 0.8167 0.02715 0.01768 0.0030 0.0996 1.0000
7.750 0.8354 0.02877 0.01939 0.0046 0.0932 1.0000
8.000 0.8517 0.02998 0.02071 0.0066 0.0872 1.0000
8.250 0.8726 0.03234 0.02301 0.0075 0.0831 1.0000
8.500 0.8853 0.03406 0.02515 0.0102 0.0808 1.0000
8.750 0.8967 0.03594 0.02736 0.0130 0.0779 1.0000
9.000 0.9099 0.03760 0.02918 0.0151 0.0748 1.0000
9.250 0.9234 0.03962 0.03124 0.0169 0.0723 1.0000
9.500 0.9315 0.04333 0.03514 0.0190 0.0710 1.0000
9.750 0.9318 0.04589 0.03811 0.0227 0.0706 1.0000
10.000 0.9301 0.04884 0.04142 0.0263 0.0705 1.0000
10.250 0.9253 0.05210 0.04499 0.0298 0.0705 1.0000
10.500 0.9179 0.05548 0.04866 0.0333 0.0706 1.0000
10.750 0.9082 0.05915 0.05256 0.0365 0.0708 1.0000
11.000 0.8963 0.06290 0.05650 0.0395 0.0710 1.0000
11.250 0.8001 0.06691 0.06120 0.0474 0.0756 1.0000
11.500 0.7484 0.07439 0.06887 0.0453 0.0779 1.0000
11.750 0.7069 0.08359 0.07813 0.0398 0.0803 1.0000
12.000 0.6937 0.09037 0.08491 0.0371 0.0822 1.0000
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Polar data table (+)
Polar graphs
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