N-13 (n13-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: N-13 (n13-il) Reynolds number: 100,000 Max Cl/Cd: 41.3 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n13-il-100000.txt Download as CSV file: xf-n13-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: N-13
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
------ -------- --------- --------- -------- -------- --------
-12.750 -0.4885 0.12853 0.12337 -0.0203 1.0000 0.1412
-12.500 -0.6828 0.10267 0.09735 -0.0307 1.0000 0.0743
-12.250 -0.7899 0.07893 0.07337 -0.0477 1.0000 0.0623
-12.000 -0.8126 0.07348 0.06783 -0.0491 1.0000 0.0620
-11.750 -0.8342 0.06870 0.06295 -0.0492 1.0000 0.0616
-11.500 -0.8585 0.06472 0.05881 -0.0478 1.0000 0.0615
-11.250 -0.8779 0.06108 0.05503 -0.0452 1.0000 0.0609
-11.000 -0.9013 0.05800 0.05176 -0.0409 1.0000 0.0608
-10.750 -0.9206 0.05496 0.04849 -0.0364 1.0000 0.0609
-10.500 -0.9357 0.05180 0.04501 -0.0320 1.0000 0.0612
-10.250 -0.9481 0.04873 0.04155 -0.0274 1.0000 0.0617
-10.000 -0.9549 0.04573 0.03812 -0.0231 1.0000 0.0622
-9.750 -0.9557 0.04226 0.03427 -0.0195 1.0000 0.0629
-9.500 -0.9460 0.03936 0.03126 -0.0174 1.0000 0.0648
-9.250 -0.9349 0.03756 0.02934 -0.0150 1.0000 0.0675
-9.000 -0.9257 0.03569 0.02717 -0.0121 1.0000 0.0712
-8.750 -0.9145 0.03350 0.02468 -0.0094 1.0000 0.0750
-8.500 -0.8993 0.03225 0.02343 -0.0074 1.0000 0.0800
-8.250 -0.8863 0.03070 0.02159 -0.0047 1.0000 0.0865
-8.000 -0.8716 0.02973 0.02061 -0.0026 1.0000 0.0940
-7.750 -0.8560 0.02830 0.01908 -0.0005 1.0000 0.1023
-7.500 -0.8425 0.02744 0.01800 0.0022 1.0000 0.1116
-7.250 -0.8248 0.02609 0.01676 0.0037 1.0000 0.1217
-7.000 -0.8078 0.02490 0.01555 0.0055 1.0000 0.1324
-6.750 -0.7909 0.02384 0.01443 0.0074 1.0000 0.1440
-6.500 -0.7735 0.02278 0.01340 0.0094 1.0000 0.1571
-6.250 -0.7577 0.02173 0.01250 0.0115 1.0000 0.1738
-6.000 -0.7439 0.02082 0.01170 0.0140 1.0000 0.1967
-5.500 -0.7151 0.01915 0.01025 0.0188 1.0000 0.2418
-5.250 -0.7011 0.01839 0.00967 0.0213 1.0000 0.2668
-5.000 -0.6885 0.01764 0.00918 0.0240 1.0000 0.3035
-4.750 -0.6778 0.01687 0.00880 0.0271 1.0000 0.3616
-4.500 -0.6685 0.01614 0.00851 0.0306 1.0000 0.4418
-4.250 -0.6573 0.01567 0.00839 0.0341 1.0000 0.5134
-4.000 -0.6435 0.01542 0.00833 0.0371 1.0000 0.5706
-3.750 -0.6286 0.01529 0.00832 0.0400 1.0000 0.6184
-3.500 -0.6135 0.01520 0.00830 0.0429 1.0000 0.6628
-3.250 -0.5965 0.01514 0.00836 0.0456 1.0000 0.7033
-3.000 -0.5785 0.01510 0.00839 0.0480 1.0000 0.7407
-2.750 -0.5557 0.01516 0.00852 0.0496 1.0000 0.7748
-2.500 -0.5299 0.01529 0.00867 0.0504 1.0000 0.8052
-2.250 -0.5000 0.01556 0.00895 0.0505 1.0000 0.8344
-2.000 -0.4635 0.01604 0.00940 0.0493 1.0000 0.8622
-1.750 -0.4201 0.01668 0.00997 0.0468 1.0000 0.8855
-1.500 -0.3785 0.01733 0.01054 0.0445 1.0000 0.9087
-1.250 -0.3145 0.01829 0.01139 0.0381 1.0000 0.9268
-1.000 -0.2492 0.01910 0.01210 0.0312 1.0000 0.9425
-0.750 -0.1900 0.01960 0.01253 0.0248 1.0000 0.9573
-0.500 -0.1283 0.01996 0.01284 0.0177 1.0000 0.9716
-0.250 -0.0682 0.02013 0.01298 0.0104 1.0000 0.9845
0.000 -0.0099 0.02016 0.01300 0.0032 1.0000 0.9962
0.250 0.0003 0.02013 0.01297 0.0037 1.0000 1.0000
0.500 0.0319 0.02013 0.01299 0.0008 0.9931 1.0000
0.750 0.0891 0.02008 0.01297 -0.0062 0.9808 1.0000
1.000 0.1442 0.01990 0.01284 -0.0125 0.9674 1.0000
1.250 0.2002 0.01958 0.01260 -0.0186 0.9532 1.0000
1.500 0.2608 0.01909 0.01220 -0.0251 0.9384 1.0000
1.750 0.3258 0.01839 0.01164 -0.0320 0.9242 1.0000
2.000 0.3966 0.01754 0.01095 -0.0397 0.9106 1.0000
2.250 0.4626 0.01672 0.01030 -0.0463 0.8926 1.0000
2.500 0.5109 0.01608 0.00978 -0.0495 0.8637 1.0000
2.750 0.5391 0.01560 0.00935 -0.0487 0.8230 1.0000
3.000 0.5643 0.01514 0.00888 -0.0472 0.7735 1.0000
3.250 0.5937 0.01488 0.00842 -0.0464 0.7182 1.0000
3.500 0.6141 0.01499 0.00830 -0.0442 0.6600 1.0000
3.750 0.6273 0.01519 0.00832 -0.0409 0.5975 1.0000
4.000 0.6384 0.01547 0.00832 -0.0373 0.5249 1.0000
4.250 0.6484 0.01597 0.00840 -0.0336 0.4522 1.0000
4.500 0.6585 0.01666 0.00869 -0.0302 0.3889 1.0000
4.750 0.6685 0.01737 0.00908 -0.0269 0.3299 1.0000
5.000 0.6783 0.01817 0.00954 -0.0236 0.2755 1.0000
5.250 0.6893 0.01906 0.01012 -0.0205 0.2317 1.0000
5.500 0.7019 0.01999 0.01080 -0.0178 0.2003 1.0000
5.750 0.7171 0.02098 0.01162 -0.0155 0.1787 1.0000
6.000 0.7335 0.02189 0.01246 -0.0134 0.1616 1.0000
6.250 0.7515 0.02291 0.01342 -0.0116 0.1486 1.0000
6.500 0.7713 0.02408 0.01441 -0.0102 0.1375 1.0000
6.750 0.7886 0.02491 0.01544 -0.0081 0.1277 1.0000
7.000 0.8089 0.02625 0.01679 -0.0067 0.1199 1.0000
7.250 0.8266 0.02727 0.01788 -0.0049 0.1120 1.0000
7.500 0.8452 0.02883 0.01958 -0.0032 0.1055 1.0000
7.750 0.8613 0.02996 0.02081 -0.0012 0.0987 1.0000
8.000 0.8781 0.03192 0.02290 0.0006 0.0936 1.0000
8.250 0.8901 0.03337 0.02467 0.0035 0.0884 1.0000
8.500 0.9062 0.03508 0.02636 0.0051 0.0835 1.0000
8.750 0.9131 0.03759 0.02926 0.0084 0.0806 1.0000
9.000 0.9158 0.03962 0.03175 0.0125 0.0775 1.0000
9.250 0.9222 0.04151 0.03386 0.0157 0.0741 1.0000
9.500 0.9315 0.04370 0.03616 0.0181 0.0719 1.0000
9.750 0.9358 0.04691 0.03951 0.0208 0.0703 1.0000
10.000 0.9284 0.05065 0.04355 0.0249 0.0694 1.0000
10.250 0.9159 0.05335 0.04662 0.0297 0.0690 1.0000
10.500 0.8990 0.05622 0.04982 0.0346 0.0686 1.0000
10.750 0.8787 0.05927 0.05312 0.0393 0.0684 1.0000
11.000 0.8560 0.06220 0.05622 0.0440 0.0686 1.0000
11.250 0.8293 0.06527 0.05945 0.0479 0.0685 1.0000
11.500 0.8072 0.06927 0.06357 0.0497 0.0689 1.0000
11.750 0.7868 0.07391 0.06829 0.0501 0.0693 1.0000
12.000 0.5998 0.12223 0.11681 0.0191 0.1517 1.0000
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Polar data table (+)
Polar graphs
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