N-14 (n14-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: N-14 (n14-il) Reynolds number: 200,000 Max Cl/Cd: 48.35 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n14-il-200000.txt Download as CSV file: xf-n14-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.5285 0.10020 0.09644 -0.0315 1.0000 0.0725
-12.000 -0.9447 0.05213 0.04701 -0.0499 1.0000 0.0438
-11.750 -0.9701 0.04918 0.04378 -0.0450 1.0000 0.0435
-11.500 -0.9862 0.04678 0.04118 -0.0400 1.0000 0.0436
-11.250 -0.9915 0.04449 0.03873 -0.0364 1.0000 0.0441
-11.000 -0.9943 0.04217 0.03620 -0.0328 1.0000 0.0445
-10.750 -0.9859 0.04085 0.03485 -0.0305 1.0000 0.0458
-10.500 -0.9846 0.03896 0.03276 -0.0271 1.0000 0.0467
-10.250 -0.9826 0.03698 0.03052 -0.0235 1.0000 0.0477
-10.000 -0.9788 0.03497 0.02821 -0.0201 1.0000 0.0485
-9.750 -0.9721 0.03310 0.02605 -0.0169 1.0000 0.0493
-9.500 -0.9632 0.03167 0.02432 -0.0138 1.0000 0.0502
-9.250 -0.9527 0.02991 0.02227 -0.0111 1.0000 0.0512
-9.000 -0.9358 0.02768 0.01999 -0.0098 1.0000 0.0530
-8.750 -0.9195 0.02648 0.01873 -0.0080 1.0000 0.0544
-8.500 -0.9030 0.02536 0.01751 -0.0061 1.0000 0.0558
-8.250 -0.8867 0.02439 0.01644 -0.0041 1.0000 0.0576
-8.000 -0.8700 0.02349 0.01540 -0.0020 1.0000 0.0593
-7.750 -0.8531 0.02262 0.01440 0.0000 1.0000 0.0606
-7.500 -0.8368 0.02125 0.01306 0.0019 1.0000 0.0626
-7.250 -0.8221 0.02055 0.01237 0.0042 1.0000 0.0648
-7.000 -0.8074 0.01996 0.01175 0.0065 1.0000 0.0672
-6.750 -0.7927 0.01939 0.01112 0.0090 1.0000 0.0698
-6.500 -0.7797 0.01870 0.01043 0.0117 1.0000 0.0723
-6.250 -0.7662 0.01823 0.01000 0.0142 1.0000 0.0757
-6.000 -0.7515 0.01787 0.00961 0.0166 1.0000 0.0803
-5.750 -0.7376 0.01746 0.00922 0.0191 1.0000 0.0863
-5.500 -0.7222 0.01714 0.00888 0.0214 1.0000 0.0955
-5.250 -0.7095 0.01656 0.00836 0.0240 1.0000 0.1109
-5.000 -0.6975 0.01591 0.00782 0.0267 1.0000 0.1309
-4.750 -0.6832 0.01548 0.00744 0.0289 1.0000 0.1484
-4.500 -0.6676 0.01516 0.00718 0.0309 1.0000 0.1641
-4.250 -0.6515 0.01489 0.00696 0.0328 1.0000 0.1803
-4.000 -0.6300 0.01460 0.00679 0.0336 0.9989 0.2016
-3.750 -0.5965 0.01431 0.00671 0.0319 0.9947 0.2442
-3.500 -0.5663 0.01390 0.00660 0.0308 0.9900 0.3063
-3.250 -0.5365 0.01343 0.00652 0.0299 0.9851 0.3820
-3.000 -0.5110 0.01291 0.00646 0.0299 0.9799 0.4759
-2.750 -0.4879 0.01239 0.00653 0.0308 0.9740 0.5935
-2.500 -0.4565 0.01221 0.00683 0.0304 0.9702 0.7013
-2.250 -0.4312 0.01213 0.00693 0.0313 0.9636 0.7577
-2.000 -0.3953 0.01222 0.00708 0.0300 0.9591 0.7988
-1.750 -0.3554 0.01232 0.00722 0.0280 0.9540 0.8313
-1.500 -0.3142 0.01240 0.00732 0.0258 0.9474 0.8562
-1.250 -0.2633 0.01250 0.00739 0.0217 0.9433 0.8756
-1.000 -0.2194 0.01262 0.00750 0.0190 0.9370 0.8915
-0.750 -0.1664 0.01272 0.00757 0.0144 0.9319 0.9014
-0.500 -0.1129 0.01270 0.00751 0.0097 0.9281 0.9110
-0.250 -0.0489 0.01284 0.00763 0.0029 0.9268 0.9152
0.000 -0.0056 0.01299 0.00778 0.0002 0.9203 0.9234
0.250 0.0503 0.01301 0.00781 -0.0051 0.9169 0.9278
0.500 0.1139 0.01302 0.00783 -0.0119 0.9144 0.9302
0.750 0.1853 0.01305 0.00791 -0.0197 0.9114 0.9374
1.000 0.2488 0.01304 0.00794 -0.0259 0.9002 0.9462
1.250 0.3030 0.01283 0.00775 -0.0306 0.8847 0.9525
1.500 0.3454 0.01259 0.00749 -0.0330 0.8643 0.9571
1.750 0.3878 0.01238 0.00728 -0.0356 0.8398 0.9603
2.000 0.4251 0.01224 0.00709 -0.0371 0.8102 0.9649
2.250 0.4543 0.01218 0.00696 -0.0370 0.7743 0.9709
2.500 0.4904 0.01203 0.00670 -0.0384 0.7246 0.9750
2.750 0.5194 0.01207 0.00649 -0.0383 0.6554 0.9807
3.000 0.5476 0.01229 0.00628 -0.0383 0.5635 0.9857
3.250 0.5747 0.01268 0.00620 -0.0384 0.4688 0.9911
3.500 0.6043 0.01303 0.00620 -0.0392 0.4038 0.9959
3.750 0.6356 0.01329 0.00623 -0.0404 0.3571 1.0000
4.000 0.6513 0.01356 0.00640 -0.0383 0.3263 1.0000
4.250 0.6672 0.01383 0.00657 -0.0363 0.2949 1.0000
4.500 0.6827 0.01412 0.00673 -0.0343 0.2570 1.0000
4.750 0.6970 0.01451 0.00691 -0.0320 0.2067 1.0000
5.000 0.7092 0.01513 0.00725 -0.0294 0.1604 1.0000
5.250 0.7202 0.01589 0.00777 -0.0265 0.1264 1.0000
5.500 0.7324 0.01655 0.00829 -0.0238 0.1091 1.0000
5.750 0.7467 0.01699 0.00872 -0.0214 0.0989 1.0000
6.000 0.7603 0.01751 0.00925 -0.0188 0.0924 1.0000
6.250 0.7746 0.01796 0.00970 -0.0163 0.0870 1.0000
6.500 0.7871 0.01863 0.01032 -0.0136 0.0827 1.0000
6.750 0.8020 0.01910 0.01086 -0.0112 0.0789 1.0000
7.000 0.8162 0.01965 0.01142 -0.0087 0.0756 1.0000
7.250 0.8295 0.02058 0.01228 -0.0063 0.0722 1.0000
7.500 0.8450 0.02128 0.01307 -0.0040 0.0696 1.0000
7.750 0.8607 0.02200 0.01386 -0.0018 0.0669 1.0000
8.000 0.8763 0.02276 0.01463 0.0004 0.0641 1.0000
8.250 0.8947 0.02453 0.01635 0.0016 0.0608 1.0000
8.500 0.9100 0.02526 0.01726 0.0040 0.0591 1.0000
8.750 0.9255 0.02622 0.01837 0.0061 0.0568 1.0000
9.000 0.9407 0.02719 0.01942 0.0082 0.0545 1.0000
9.250 0.9573 0.02854 0.02075 0.0098 0.0521 1.0000
9.500 0.9718 0.03110 0.02351 0.0116 0.0503 1.0000
9.750 0.9809 0.03214 0.02483 0.0148 0.0489 1.0000
10.000 0.9897 0.03351 0.02645 0.0178 0.0473 1.0000
10.250 0.9992 0.03485 0.02795 0.0205 0.0456 1.0000
10.500 1.0103 0.03614 0.02928 0.0227 0.0440 1.0000
10.750 1.0202 0.03828 0.03149 0.0247 0.0429 1.0000
11.000 1.0196 0.04238 0.03584 0.0276 0.0420 1.0000
11.250 1.0114 0.04373 0.03755 0.0326 0.0415 1.0000
11.500 1.0009 0.04565 0.03976 0.0374 0.0410 1.0000
11.750 0.9844 0.04755 0.04191 0.0428 0.0406 1.0000
12.000 0.9658 0.04984 0.04443 0.0475 0.0403 1.0000
12.250 0.9449 0.05256 0.04739 0.0512 0.0399 1.0000
12.500 0.9222 0.05590 0.05096 0.0535 0.0397 1.0000
12.750 0.8975 0.06011 0.05537 0.0543 0.0399 1.0000
13.000 0.8691 0.06532 0.06079 0.0535 0.0402 1.0000
13.250 0.8403 0.07152 0.06715 0.0508 0.0405 1.0000
13.500 0.8103 0.07919 0.07495 0.0464 0.0411 1.0000
13.750 0.7854 0.08738 0.08321 0.0420 0.0417 1.0000
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Polar data table (+)
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