N-9 (n9-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: N-9 (n9-il) Reynolds number: 50,000 Max Cl/Cd: 38.32 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n9-il-50000-n5.txt Download as CSV file: xf-n9-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: N-9
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.4756 0.12028 0.11312 -0.0126 1.0000 0.0982
-10.750 -0.4784 0.11714 0.11006 -0.0154 1.0000 0.0987
-10.500 -0.4790 0.11362 0.10661 -0.0178 1.0000 0.0989
-10.250 -0.4785 0.10988 0.10294 -0.0199 1.0000 0.0990
-9.750 -0.4699 0.09580 0.08886 -0.0254 1.0000 0.0580
-9.500 -0.4656 0.09202 0.08513 -0.0257 1.0000 0.0572
-9.250 -0.4632 0.08807 0.08124 -0.0271 1.0000 0.0563
-9.000 -0.4607 0.08375 0.07697 -0.0296 1.0000 0.0554
-8.750 -0.4580 0.07915 0.07241 -0.0327 1.0000 0.0547
-8.500 -0.4548 0.07430 0.06757 -0.0358 1.0000 0.0540
-8.250 -0.4507 0.06933 0.06256 -0.0389 1.0000 0.0538
-8.000 -0.4453 0.06429 0.05744 -0.0417 1.0000 0.0543
-7.750 -0.4383 0.05920 0.05217 -0.0441 1.0000 0.0553
-7.500 -0.4293 0.05407 0.04676 -0.0460 1.0000 0.0562
-7.250 -0.4176 0.04912 0.04140 -0.0473 1.0000 0.0569
-7.000 -0.4030 0.04458 0.03636 -0.0479 1.0000 0.0575
-6.750 -0.3865 0.04075 0.03205 -0.0480 1.0000 0.0593
-6.500 -0.3689 0.03910 0.03039 -0.0472 1.0000 0.0635
-6.250 -0.3490 0.03619 0.02699 -0.0469 1.0000 0.0671
-6.000 -0.3271 0.03320 0.02336 -0.0465 1.0000 0.0698
-5.750 -0.3061 0.03134 0.02126 -0.0459 1.0000 0.0752
-5.500 -0.2836 0.02964 0.01922 -0.0451 1.0000 0.0806
-5.250 -0.2593 0.02782 0.01683 -0.0443 1.0000 0.0846
-5.000 -0.2371 0.02655 0.01552 -0.0437 1.0000 0.0915
-4.750 -0.2131 0.02542 0.01403 -0.0428 1.0000 0.0995
-4.500 -0.1897 0.02420 0.01281 -0.0421 1.0000 0.1056
-4.250 -0.1656 0.02325 0.01162 -0.0413 1.0000 0.1139
-4.000 -0.1418 0.02246 0.01079 -0.0407 1.0000 0.1276
-3.750 -0.1180 0.02180 0.01024 -0.0404 1.0000 0.1467
-3.500 -0.0941 0.02130 0.00981 -0.0401 1.0000 0.1726
-3.250 -0.0697 0.02080 0.00946 -0.0400 1.0000 0.2192
-3.000 -0.0443 0.01996 0.00913 -0.0403 1.0000 0.3097
-2.750 -0.0204 0.01850 0.00909 -0.0397 0.9979 0.6030
-2.500 0.0220 0.01784 0.00885 -0.0416 0.9863 1.0000
-2.250 0.0627 0.01808 0.00870 -0.0447 0.9760 1.0000
-2.000 0.1027 0.01831 0.00862 -0.0475 0.9653 1.0000
-1.750 0.1414 0.01852 0.00856 -0.0501 0.9539 1.0000
-1.500 0.1811 0.01870 0.00854 -0.0528 0.9417 1.0000
-1.250 0.2261 0.01878 0.00842 -0.0561 0.9274 1.0000
-1.000 0.2734 0.01875 0.00825 -0.0596 0.9123 1.0000
-0.750 0.3164 0.01871 0.00808 -0.0622 0.8966 1.0000
-0.500 0.3537 0.01874 0.00803 -0.0637 0.8814 1.0000
-0.250 0.3852 0.01886 0.00809 -0.0642 0.8656 1.0000
0.000 0.4150 0.01899 0.00818 -0.0644 0.8492 1.0000
0.250 0.4441 0.01911 0.00828 -0.0644 0.8326 1.0000
0.500 0.4730 0.01921 0.00837 -0.0642 0.8159 1.0000
0.750 0.5021 0.01927 0.00843 -0.0641 0.7991 1.0000
1.000 0.5315 0.01931 0.00847 -0.0638 0.7827 1.0000
1.250 0.5590 0.01940 0.00859 -0.0633 0.7643 1.0000
1.500 0.5870 0.01948 0.00868 -0.0628 0.7459 1.0000
1.750 0.6153 0.01958 0.00879 -0.0622 0.7275 1.0000
2.000 0.6437 0.01970 0.00893 -0.0617 0.7088 1.0000
2.250 0.6696 0.01994 0.00920 -0.0609 0.6865 1.0000
2.500 0.6960 0.02013 0.00938 -0.0599 0.6624 1.0000
2.750 0.7204 0.02036 0.00965 -0.0587 0.6344 1.0000
3.000 0.7438 0.02060 0.00988 -0.0574 0.6040 1.0000
3.250 0.7665 0.02086 0.01015 -0.0560 0.5719 1.0000
3.500 0.7891 0.02116 0.01047 -0.0547 0.5397 1.0000
3.750 0.8116 0.02148 0.01080 -0.0534 0.5069 1.0000
4.000 0.8334 0.02184 0.01109 -0.0520 0.4728 1.0000
4.250 0.8550 0.02231 0.01146 -0.0507 0.4397 1.0000
4.500 0.8763 0.02288 0.01202 -0.0495 0.4082 1.0000
4.750 0.8968 0.02356 0.01265 -0.0483 0.3751 1.0000
5.000 0.9166 0.02433 0.01338 -0.0470 0.3413 1.0000
5.250 0.9355 0.02520 0.01422 -0.0457 0.3061 1.0000
5.500 0.9535 0.02617 0.01519 -0.0444 0.2655 1.0000
5.750 0.9711 0.02724 0.01623 -0.0431 0.2282 1.0000
6.000 0.9889 0.02841 0.01728 -0.0418 0.2032 1.0000
6.250 1.0078 0.02960 0.01848 -0.0407 0.1863 1.0000
6.500 1.0265 0.03084 0.01972 -0.0397 0.1727 1.0000
6.750 1.0450 0.03213 0.02101 -0.0386 0.1615 1.0000
7.000 1.0655 0.03347 0.02250 -0.0377 0.1523 1.0000
7.250 1.0855 0.03494 0.02415 -0.0368 0.1431 1.0000
7.500 1.1055 0.03656 0.02576 -0.0359 0.1343 1.0000
7.750 1.1249 0.03830 0.02778 -0.0350 0.1247 1.0000
8.000 1.1408 0.04025 0.02993 -0.0339 0.1136 1.0000
8.250 1.1519 0.04215 0.03195 -0.0325 0.1013 1.0000
8.500 1.1603 0.04400 0.03388 -0.0309 0.0899 1.0000
8.750 1.1667 0.04599 0.03620 -0.0290 0.0799 1.0000
9.000 1.1716 0.04847 0.03904 -0.0270 0.0711 1.0000
9.250 1.1766 0.05039 0.04100 -0.0253 0.0649 1.0000
9.500 1.1740 0.05347 0.04461 -0.0228 0.0591 1.0000
9.750 1.1724 0.05582 0.04713 -0.0208 0.0551 1.0000
10.000 1.1722 0.05842 0.04975 -0.0193 0.0524 1.0000
10.250 1.1622 0.06266 0.05447 -0.0179 0.0504 1.0000
10.500 1.1495 0.06705 0.05921 -0.0173 0.0488 1.0000
10.750 1.1346 0.07183 0.06428 -0.0175 0.0478 1.0000
11.000 1.1170 0.07734 0.07004 -0.0189 0.0472 1.0000
11.250 1.0954 0.08395 0.07690 -0.0215 0.0472 1.0000
11.500 1.0691 0.09213 0.08528 -0.0256 0.0479 1.0000
11.750 1.0398 0.10189 0.09520 -0.0313 0.0492 1.0000
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Polar data table (+)
Polar graphs
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