N-14 (n14-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: N-14 (n14-il) Reynolds number: 100,000 Max Cl/Cd: 40.54 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n14-il-100000.txt Download as CSV file: xf-n14-il-100000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.8386 0.07009 0.06409 -0.0434 1.0000 0.0821
-10.750 -0.8558 0.06631 0.06020 -0.0402 1.0000 0.0819
-10.500 -0.8666 0.06236 0.05613 -0.0375 1.0000 0.0815
-10.250 -0.8786 0.05868 0.05227 -0.0342 1.0000 0.0813
-10.000 -0.8883 0.05508 0.04845 -0.0307 1.0000 0.0809
-9.750 -0.8963 0.05161 0.04471 -0.0270 1.0000 0.0807
-9.500 -0.9015 0.04833 0.04112 -0.0232 1.0000 0.0806
-9.250 -0.9054 0.04548 0.03788 -0.0191 1.0000 0.0811
-9.000 -0.9075 0.04312 0.03505 -0.0148 1.0000 0.0819
-8.750 -0.8990 0.04013 0.03194 -0.0125 1.0000 0.0835
-8.500 -0.8861 0.03811 0.02983 -0.0104 1.0000 0.0852
-8.250 -0.8740 0.03613 0.02763 -0.0080 1.0000 0.0866
-8.000 -0.8614 0.03443 0.02570 -0.0055 1.0000 0.0889
-7.750 -0.8492 0.03291 0.02386 -0.0028 1.0000 0.0918
-7.500 -0.8366 0.03150 0.02206 0.0001 1.0000 0.0941
-7.250 -0.8173 0.02941 0.01989 0.0015 1.0000 0.0967
-7.000 -0.7982 0.02806 0.01850 0.0029 1.0000 0.1003
-6.750 -0.7807 0.02699 0.01728 0.0049 1.0000 0.1054
-6.500 -0.7609 0.02559 0.01575 0.0064 1.0000 0.1106
-6.250 -0.7409 0.02433 0.01458 0.0078 1.0000 0.1173
-6.000 -0.7216 0.02303 0.01324 0.0094 1.0000 0.1262
-5.750 -0.7054 0.02184 0.01217 0.0115 1.0000 0.1405
-5.500 -0.6923 0.02069 0.01126 0.0140 1.0000 0.1618
-5.250 -0.6804 0.01979 0.01055 0.0168 1.0000 0.1897
-5.000 -0.6668 0.01920 0.01005 0.0193 1.0000 0.2156
-4.750 -0.6525 0.01869 0.00964 0.0217 1.0000 0.2405
-4.500 -0.6385 0.01815 0.00927 0.0240 1.0000 0.2678
-4.250 -0.6250 0.01757 0.00890 0.0265 1.0000 0.3067
-4.000 -0.6139 0.01681 0.00853 0.0294 1.0000 0.3623
-3.750 -0.6046 0.01602 0.00826 0.0328 1.0000 0.4420
-3.500 -0.5961 0.01529 0.00821 0.0368 1.0000 0.5527
-3.250 -0.5819 0.01497 0.00848 0.0404 1.0000 0.6709
-3.000 -0.5618 0.01510 0.00885 0.0430 1.0000 0.7542
-2.750 -0.5368 0.01542 0.00919 0.0446 1.0000 0.8088
-2.500 -0.5055 0.01587 0.00960 0.0449 1.0000 0.8500
-2.250 -0.4660 0.01647 0.01009 0.0436 1.0000 0.8812
-2.000 -0.4120 0.01731 0.01079 0.0395 1.0000 0.9054
-1.750 -0.3544 0.01814 0.01146 0.0344 1.0000 0.9257
-1.500 -0.2897 0.01891 0.01209 0.0278 1.0000 0.9413
-1.250 -0.2270 0.01944 0.01248 0.0211 1.0000 0.9550
-1.000 -0.1635 0.01985 0.01280 0.0140 1.0000 0.9701
-0.750 -0.0895 0.02005 0.01292 0.0047 1.0000 0.9843
-0.500 -0.0090 0.02000 0.01282 -0.0060 1.0000 0.9991
-0.250 -0.0053 0.01997 0.01278 -0.0034 1.0000 1.0000
0.000 -0.0072 0.01997 0.01276 0.0002 1.0000 1.0000
0.250 -0.0089 0.01998 0.01277 0.0038 1.0000 1.0000
0.500 0.0358 0.02007 0.01288 -0.0008 0.9921 1.0000
0.750 0.0919 0.02014 0.01298 -0.0072 0.9813 1.0000
1.000 0.1487 0.02012 0.01301 -0.0136 0.9704 1.0000
1.250 0.2013 0.01994 0.01290 -0.0190 0.9577 1.0000
1.750 0.3140 0.01918 0.01236 -0.0301 0.9297 1.0000
2.000 0.4029 0.01792 0.01129 -0.0404 0.9122 1.0000
2.250 0.4623 0.01689 0.01040 -0.0452 0.8873 1.0000
2.500 0.5120 0.01611 0.00975 -0.0483 0.8609 1.0000
2.750 0.5461 0.01557 0.00925 -0.0483 0.8226 1.0000
3.000 0.5718 0.01520 0.00884 -0.0467 0.7730 1.0000
3.250 0.5904 0.01500 0.00853 -0.0438 0.7094 1.0000
3.500 0.6079 0.01501 0.00821 -0.0408 0.6284 1.0000
3.750 0.6223 0.01535 0.00812 -0.0377 0.5479 1.0000
4.000 0.6350 0.01583 0.00822 -0.0346 0.4812 1.0000
4.250 0.6479 0.01634 0.00843 -0.0317 0.4276 1.0000
4.500 0.6610 0.01689 0.00873 -0.0290 0.3824 1.0000
4.750 0.6734 0.01748 0.00908 -0.0262 0.3393 1.0000
5.000 0.6853 0.01806 0.00948 -0.0233 0.2931 1.0000
5.250 0.6958 0.01870 0.00989 -0.0202 0.2420 1.0000
5.500 0.7051 0.01961 0.01046 -0.0169 0.1933 1.0000
5.750 0.7159 0.02072 0.01128 -0.0139 0.1635 1.0000
6.000 0.7298 0.02174 0.01216 -0.0114 0.1460 1.0000
6.250 0.7465 0.02284 0.01317 -0.0094 0.1352 1.0000
6.500 0.7643 0.02384 0.01408 -0.0076 0.1262 1.0000
6.750 0.7832 0.02494 0.01526 -0.0059 0.1188 1.0000
7.000 0.8029 0.02604 0.01635 -0.0044 0.1129 1.0000
7.250 0.8235 0.02752 0.01786 -0.0031 0.1079 1.0000
7.500 0.8406 0.02861 0.01917 -0.0010 0.1027 1.0000
7.750 0.8595 0.02995 0.02054 0.0005 0.0987 1.0000
8.000 0.8773 0.03186 0.02256 0.0021 0.0950 1.0000
8.250 0.8894 0.03326 0.02432 0.0049 0.0914 1.0000
8.500 0.9031 0.03500 0.02632 0.0073 0.0888 1.0000
8.750 0.9181 0.03661 0.02799 0.0093 0.0857 1.0000
9.000 0.9297 0.03924 0.03073 0.0113 0.0832 1.0000
9.250 0.9312 0.04140 0.03338 0.0154 0.0817 1.0000
9.500 0.9310 0.04412 0.03652 0.0194 0.0807 1.0000
9.750 0.9271 0.04694 0.03974 0.0235 0.0798 1.0000
10.000 0.9195 0.04988 0.04302 0.0277 0.0788 1.0000
10.250 0.9079 0.05301 0.04645 0.0320 0.0783 1.0000
10.500 0.8911 0.05627 0.04997 0.0364 0.0780 1.0000
10.750 0.8672 0.05966 0.05359 0.0410 0.0785 1.0000
11.000 0.8396 0.06312 0.05721 0.0453 0.0794 1.0000
11.250 0.8091 0.06727 0.06150 0.0476 0.0802 1.0000
11.500 0.7823 0.07215 0.06650 0.0479 0.0813 1.0000
11.750 0.7619 0.07756 0.07196 0.0468 0.0823 1.0000
12.000 0.7567 0.08291 0.07731 0.0462 0.0833 1.0000
12.250 0.6255 0.12669 0.12116 0.0186 0.1537 1.0000
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Polar data table (+)
Polar graphs
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