N-14 (n14-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: N-14 (n14-il) Reynolds number: 100,000 Max Cl/Cd: 36.78 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n14-il-100000-n5.txt Download as CSV file: xf-n14-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: N-14
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
------ -------- --------- --------- -------- -------- --------
-13.250 -0.7819 0.08136 0.07560 -0.0426 1.0000 0.0419
-13.000 -0.8500 0.06752 0.06142 -0.0518 1.0000 0.0404
-12.750 -0.8784 0.06183 0.05551 -0.0535 1.0000 0.0404
-12.500 -0.9007 0.05750 0.05095 -0.0534 1.0000 0.0405
-12.250 -0.9170 0.05420 0.04745 -0.0521 1.0000 0.0409
-12.000 -0.9309 0.05135 0.04440 -0.0499 1.0000 0.0415
-11.750 -0.9429 0.04880 0.04162 -0.0470 1.0000 0.0421
-11.500 -0.9531 0.04650 0.03909 -0.0435 1.0000 0.0427
-11.250 -0.9613 0.04448 0.03681 -0.0395 1.0000 0.0434
-11.000 -0.9667 0.04253 0.03458 -0.0356 1.0000 0.0445
-10.750 -0.9676 0.04066 0.03235 -0.0320 1.0000 0.0455
-10.500 -0.9632 0.03870 0.03016 -0.0293 1.0000 0.0466
-10.250 -0.9531 0.03693 0.02833 -0.0272 1.0000 0.0479
-10.000 -0.9425 0.03550 0.02681 -0.0250 1.0000 0.0491
-9.750 -0.9314 0.03419 0.02538 -0.0228 1.0000 0.0508
-9.500 -0.9192 0.03291 0.02393 -0.0206 1.0000 0.0526
-9.250 -0.9053 0.03156 0.02237 -0.0185 1.0000 0.0542
-9.000 -0.8900 0.03026 0.02085 -0.0166 1.0000 0.0555
-8.750 -0.8746 0.02899 0.01949 -0.0148 1.0000 0.0569
-8.500 -0.8610 0.02795 0.01846 -0.0127 1.0000 0.0588
-8.250 -0.8470 0.02710 0.01758 -0.0105 1.0000 0.0610
-8.000 -0.8323 0.02623 0.01664 -0.0083 1.0000 0.0633
-7.750 -0.8176 0.02537 0.01566 -0.0061 1.0000 0.0654
-7.500 -0.8038 0.02454 0.01480 -0.0037 1.0000 0.0675
-7.250 -0.7903 0.02386 0.01414 -0.0013 1.0000 0.0700
-7.000 -0.7760 0.02326 0.01351 0.0010 1.0000 0.0735
-6.750 -0.7615 0.02269 0.01292 0.0033 1.0000 0.0785
-6.500 -0.7468 0.02218 0.01238 0.0056 1.0000 0.0850
-6.250 -0.7325 0.02163 0.01179 0.0080 1.0000 0.0931
-6.000 -0.7179 0.02110 0.01119 0.0103 1.0000 0.1032
-5.750 -0.7041 0.02055 0.01061 0.0128 1.0000 0.1142
-5.500 -0.6906 0.02000 0.01008 0.0152 1.0000 0.1245
-5.250 -0.6761 0.01955 0.00961 0.0174 1.0000 0.1355
-5.000 -0.6613 0.01912 0.00922 0.0196 1.0000 0.1478
-4.750 -0.6465 0.01872 0.00889 0.0218 1.0000 0.1626
-4.500 -0.6311 0.01835 0.00860 0.0238 1.0000 0.1794
-4.250 -0.6134 0.01797 0.00833 0.0254 0.9994 0.2053
-4.000 -0.5827 0.01752 0.00812 0.0242 0.9946 0.2517
-3.750 -0.5541 0.01701 0.00789 0.0234 0.9894 0.3064
-3.500 -0.5247 0.01654 0.00769 0.0226 0.9845 0.3670
-3.250 -0.4981 0.01608 0.00750 0.0225 0.9788 0.4251
-3.000 -0.4687 0.01570 0.00741 0.0220 0.9739 0.4901
-2.750 -0.4421 0.01536 0.00736 0.0222 0.9681 0.5602
-2.500 -0.4112 0.01518 0.00744 0.0218 0.9632 0.6300
-2.250 -0.3752 0.01515 0.00763 0.0206 0.9598 0.6962
-2.000 -0.3448 0.01519 0.00777 0.0205 0.9539 0.7460
-1.750 -0.3083 0.01531 0.00793 0.0191 0.9496 0.7842
-1.500 -0.2674 0.01546 0.00807 0.0168 0.9464 0.8120
-1.250 -0.2359 0.01558 0.00819 0.0164 0.9396 0.8365
-1.000 -0.1909 0.01573 0.00831 0.0133 0.9346 0.8549
-0.750 -0.1461 0.01579 0.00834 0.0103 0.9278 0.8695
-0.500 -0.1009 0.01581 0.00833 0.0073 0.9193 0.8836
-0.250 -0.0457 0.01588 0.00839 0.0026 0.9119 0.8958
0.000 0.0128 0.01600 0.00852 -0.0027 0.9038 0.9084
0.250 0.0728 0.01618 0.00871 -0.0084 0.8981 0.9210
0.500 0.1174 0.01625 0.00881 -0.0113 0.8891 0.9323
0.750 0.1666 0.01616 0.00874 -0.0154 0.8802 0.9370
1.000 0.2088 0.01601 0.00862 -0.0182 0.8694 0.9423
1.250 0.2465 0.01588 0.00852 -0.0200 0.8555 0.9476
1.500 0.2892 0.01570 0.00839 -0.0228 0.8398 0.9511
1.750 0.3280 0.01552 0.00822 -0.0247 0.8176 0.9556
2.000 0.3619 0.01537 0.00805 -0.0254 0.7865 0.9608
2.250 0.3983 0.01520 0.00782 -0.0266 0.7414 0.9646
2.500 0.4303 0.01514 0.00769 -0.0271 0.6919 0.9699
2.750 0.4626 0.01515 0.00753 -0.0276 0.6344 0.9745
3.000 0.4938 0.01532 0.00739 -0.0281 0.5603 0.9789
3.250 0.5199 0.01572 0.00740 -0.0277 0.4806 0.9845
3.500 0.5483 0.01616 0.00746 -0.0282 0.4121 0.9892
3.750 0.5769 0.01656 0.00764 -0.0287 0.3657 0.9943
4.000 0.6074 0.01691 0.00782 -0.0297 0.3244 0.9990
4.250 0.6267 0.01724 0.00805 -0.0284 0.2913 1.0000
4.500 0.6427 0.01756 0.00828 -0.0264 0.2594 1.0000
4.750 0.6583 0.01790 0.00854 -0.0243 0.2261 1.0000
5.000 0.6731 0.01832 0.00882 -0.0222 0.1933 1.0000
5.250 0.6873 0.01883 0.00917 -0.0199 0.1647 1.0000
5.500 0.7013 0.01938 0.00961 -0.0176 0.1419 1.0000
5.750 0.7152 0.01995 0.01013 -0.0152 0.1239 1.0000
6.000 0.7288 0.02055 0.01070 -0.0127 0.1105 1.0000
6.250 0.7418 0.02120 0.01128 -0.0102 0.1011 1.0000
6.500 0.7561 0.02175 0.01189 -0.0078 0.0927 1.0000
6.750 0.7692 0.02238 0.01250 -0.0052 0.0869 1.0000
7.000 0.7832 0.02298 0.01319 -0.0028 0.0822 1.0000
7.250 0.7965 0.02365 0.01388 -0.0003 0.0787 1.0000
7.500 0.8089 0.02443 0.01463 0.0023 0.0758 1.0000
7.750 0.8232 0.02517 0.01548 0.0046 0.0728 1.0000
8.000 0.8373 0.02593 0.01630 0.0069 0.0696 1.0000
8.250 0.8507 0.02676 0.01714 0.0092 0.0669 1.0000
8.500 0.8643 0.02789 0.01822 0.0114 0.0647 1.0000
8.750 0.8799 0.02886 0.01939 0.0134 0.0623 1.0000
9.000 0.8944 0.02989 0.02056 0.0155 0.0596 1.0000
9.250 0.9083 0.03096 0.02171 0.0175 0.0571 1.0000
9.500 0.9217 0.03214 0.02289 0.0195 0.0548 1.0000
9.750 0.9352 0.03374 0.02460 0.0213 0.0526 1.0000
10.000 0.9460 0.03506 0.02621 0.0238 0.0506 1.0000
10.250 0.9550 0.03650 0.02788 0.0264 0.0484 1.0000
10.500 0.9629 0.03783 0.02935 0.0289 0.0464 1.0000
10.750 0.9707 0.03917 0.03074 0.0313 0.0447 1.0000
11.000 0.9798 0.04117 0.03273 0.0332 0.0432 1.0000
11.250 0.9757 0.04293 0.03486 0.0372 0.0421 1.0000
11.500 0.9682 0.04481 0.03704 0.0414 0.0410 1.0000
11.750 0.9603 0.04682 0.03933 0.0451 0.0400 1.0000
12.000 0.9520 0.04899 0.04172 0.0481 0.0390 1.0000
12.250 0.9433 0.05127 0.04419 0.0504 0.0381 1.0000
12.500 0.9347 0.05366 0.04673 0.0522 0.0371 1.0000
12.750 0.9255 0.05639 0.04959 0.0533 0.0365 1.0000
13.000 0.9155 0.05942 0.05275 0.0538 0.0360 1.0000
13.250 0.9011 0.06325 0.05674 0.0535 0.0357 1.0000
13.500 0.8807 0.06821 0.06189 0.0520 0.0356 1.0000
13.750 0.8462 0.07595 0.06991 0.0477 0.0358 1.0000
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Polar data table (+)
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