N-12 (n12-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: N-12 (n12-il) Reynolds number: 100,000 Max Cl/Cd: 38.99 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n12-il-100000.txt Download as CSV file: xf-n12-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: N-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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.6109 0.09082 0.08562 -0.0134 1.0000 0.1717
-9.250 -0.7232 0.05225 0.04692 -0.0331 1.0000 0.0900
-9.000 -0.7988 0.05855 0.05275 -0.0263 1.0000 0.0883
-8.750 -0.8349 0.05165 0.04498 -0.0206 1.0000 0.0790
-8.500 -0.8328 0.04784 0.04092 -0.0179 1.0000 0.0784
-8.250 -0.8291 0.04435 0.03711 -0.0151 1.0000 0.0778
-8.000 -0.8226 0.04092 0.03333 -0.0122 1.0000 0.0768
-7.750 -0.8140 0.03761 0.02962 -0.0094 1.0000 0.0755
-7.500 -0.8023 0.03460 0.02618 -0.0067 1.0000 0.0746
-7.250 -0.7870 0.03230 0.02350 -0.0045 1.0000 0.0754
-7.000 -0.7697 0.03035 0.02123 -0.0024 1.0000 0.0769
-6.750 -0.7497 0.02842 0.01900 -0.0007 1.0000 0.0780
-6.500 -0.7273 0.02663 0.01699 0.0006 1.0000 0.0787
-6.250 -0.7043 0.02517 0.01532 0.0018 1.0000 0.0800
-6.000 -0.6824 0.02373 0.01398 0.0029 1.0000 0.0832
-5.750 -0.6614 0.02271 0.01297 0.0043 1.0000 0.0867
-5.500 -0.6406 0.02168 0.01190 0.0059 1.0000 0.0895
-5.250 -0.6213 0.02076 0.01093 0.0077 1.0000 0.0928
-5.000 -0.6051 0.01985 0.01011 0.0099 1.0000 0.0976
-4.750 -0.5877 0.01919 0.00942 0.0121 1.0000 0.1061
-4.500 -0.5726 0.01838 0.00869 0.0145 1.0000 0.1193
-4.250 -0.5594 0.01733 0.00788 0.0172 1.0000 0.1496
-4.000 -0.5499 0.01593 0.00717 0.0203 1.0000 0.2407
-3.750 -0.5397 0.01504 0.00695 0.0234 1.0000 0.3811
-3.500 -0.5258 0.01452 0.00673 0.0262 1.0000 0.4546
-3.250 -0.5121 0.01402 0.00663 0.0291 1.0000 0.5288
-3.000 -0.4971 0.01365 0.00669 0.0321 1.0000 0.6180
-2.750 -0.4780 0.01347 0.00677 0.0344 1.0000 0.6956
-2.500 -0.4525 0.01348 0.00699 0.0358 1.0000 0.7679
-2.250 -0.4234 0.01366 0.00724 0.0364 1.0000 0.8272
-2.000 -0.3815 0.01405 0.00760 0.0348 1.0000 0.8811
-1.750 -0.2796 0.01543 0.00881 0.0232 1.0000 0.9315
-1.500 -0.1891 0.01620 0.00936 0.0123 1.0000 0.9540
-1.250 -0.1123 0.01646 0.00945 0.0029 1.0000 0.9735
-1.000 -0.0360 0.01632 0.00920 -0.0069 1.0000 0.9897
-0.750 0.0175 0.01603 0.00885 -0.0130 1.0000 1.0000
-0.500 0.0174 0.01590 0.00874 -0.0093 1.0000 1.0000
-0.250 0.0127 0.01587 0.00872 -0.0049 1.0000 1.0000
0.000 0.0054 0.01591 0.00876 -0.0001 1.0000 1.0000
0.250 -0.0025 0.01601 0.00886 0.0047 1.0000 1.0000
0.500 0.0239 0.01617 0.00904 0.0034 0.9946 1.0000
0.750 0.0867 0.01623 0.00913 -0.0041 0.9814 1.0000
1.000 0.1458 0.01611 0.00908 -0.0107 0.9658 1.0000
1.250 0.2091 0.01580 0.00887 -0.0177 0.9487 1.0000
1.500 0.2760 0.01527 0.00848 -0.0249 0.9319 1.0000
1.750 0.3399 0.01473 0.00807 -0.0314 0.9105 1.0000
2.000 0.4032 0.01421 0.00768 -0.0376 0.8829 1.0000
2.250 0.4503 0.01392 0.00744 -0.0407 0.8434 1.0000
2.500 0.4832 0.01377 0.00728 -0.0408 0.7948 1.0000
2.750 0.5061 0.01374 0.00715 -0.0390 0.7373 1.0000
3.000 0.5253 0.01382 0.00698 -0.0364 0.6711 1.0000
3.250 0.5414 0.01406 0.00692 -0.0334 0.6020 1.0000
3.500 0.5571 0.01439 0.00698 -0.0307 0.5440 1.0000
3.750 0.5725 0.01472 0.00712 -0.0281 0.4918 1.0000
4.000 0.5875 0.01507 0.00726 -0.0255 0.4422 1.0000
4.250 0.6024 0.01545 0.00746 -0.0229 0.3957 1.0000
4.500 0.6159 0.01593 0.00773 -0.0202 0.3407 1.0000
4.750 0.6245 0.01685 0.00816 -0.0166 0.2298 1.0000
5.000 0.6310 0.01846 0.00891 -0.0128 0.1345 1.0000
5.250 0.6424 0.01971 0.01000 -0.0097 0.1183 1.0000
5.500 0.6560 0.02098 0.01116 -0.0071 0.1081 1.0000
5.750 0.6739 0.02207 0.01221 -0.0052 0.1010 1.0000
6.000 0.6950 0.02368 0.01370 -0.0039 0.0962 1.0000
6.250 0.7164 0.02471 0.01489 -0.0024 0.0920 1.0000
6.500 0.7372 0.02592 0.01614 -0.0010 0.0868 1.0000
6.750 0.7618 0.02825 0.01835 -0.0006 0.0835 1.0000
7.000 0.7813 0.02960 0.02004 0.0013 0.0819 1.0000
7.250 0.7991 0.03106 0.02185 0.0034 0.0793 1.0000
7.500 0.8159 0.03274 0.02379 0.0055 0.0767 1.0000
7.750 0.8314 0.03489 0.02626 0.0077 0.0757 1.0000
8.000 0.8441 0.03731 0.02903 0.0102 0.0751 1.0000
8.250 0.8575 0.03963 0.03154 0.0123 0.0735 1.0000
8.500 0.8706 0.04265 0.03466 0.0139 0.0717 1.0000
8.750 0.8771 0.04587 0.03821 0.0167 0.0716 1.0000
9.000 0.8610 0.04926 0.04254 0.0227 0.0749 1.0000
9.250 0.8475 0.05385 0.04760 0.0268 0.0782 1.0000
9.500 0.8395 0.05828 0.05227 0.0296 0.0808 1.0000
9.750 0.7922 0.06447 0.05899 0.0343 0.0896 1.0000
10.000 0.4913 0.09398 0.08892 0.0143 0.1975 1.0000
10.250 0.5860 0.07454 0.06955 0.0313 0.1033 1.0000
10.500 0.6061 0.07352 0.06852 0.0352 0.0943 1.0000
10.750 0.6117 0.10990 0.10452 0.0094 0.1681 1.0000
11.000 0.5962 0.11450 0.10904 0.0064 0.1614 1.0000
11.250 0.6236 0.11674 0.11134 0.0098 0.1537 1.0000
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Polar data table (+)
Polar graphs
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