N-9 (n9-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: N-9 (n9-il) Reynolds number: 1,000,000 Max Cl/Cd: 92.36 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n9-il-1000000-n5.txt Download as CSV file: xf-n9-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.9329 0.03198 0.02938 -0.0642 1.0000 0.0041
-12.750 -0.9256 0.02849 0.02560 -0.0638 1.0000 0.0041
-12.500 -0.9128 0.02607 0.02294 -0.0632 1.0000 0.0042
-12.250 -0.8968 0.02422 0.02089 -0.0624 1.0000 0.0043
-12.000 -0.8789 0.02272 0.01920 -0.0615 1.0000 0.0044
-11.750 -0.8594 0.02148 0.01781 -0.0607 1.0000 0.0044
-11.500 -0.8410 0.01996 0.01609 -0.0598 1.0000 0.0046
-11.250 -0.8213 0.01864 0.01461 -0.0589 1.0000 0.0048
-11.000 -0.7996 0.01769 0.01353 -0.0581 0.9999 0.0050
-10.750 -0.7700 0.01677 0.01249 -0.0589 0.9984 0.0052
-10.500 -0.7403 0.01597 0.01158 -0.0597 0.9968 0.0054
-10.000 -0.6811 0.01451 0.00990 -0.0609 0.9925 0.0058
-9.750 -0.6515 0.01386 0.00914 -0.0615 0.9887 0.0061
-9.500 -0.6219 0.01327 0.00846 -0.0620 0.9843 0.0063
-9.250 -0.5927 0.01276 0.00784 -0.0623 0.9784 0.0065
-9.000 -0.5625 0.01206 0.00705 -0.0629 0.9711 0.0070
-8.750 -0.5295 0.01153 0.00645 -0.0641 0.9615 0.0075
-8.500 -0.4941 0.01107 0.00594 -0.0658 0.9504 0.0081
-8.250 -0.4600 0.01068 0.00546 -0.0671 0.9382 0.0087
-8.000 -0.4298 0.01037 0.00505 -0.0675 0.9266 0.0092
-7.750 -0.4020 0.00999 0.00457 -0.0674 0.9167 0.0104
-7.500 -0.3746 0.00971 0.00424 -0.0672 0.9086 0.0115
-7.250 -0.3472 0.00947 0.00393 -0.0670 0.9019 0.0125
-6.750 -0.2922 0.00902 0.00344 -0.0667 0.8903 0.0166
-6.500 -0.2645 0.00886 0.00323 -0.0665 0.8844 0.0184
-6.250 -0.2369 0.00865 0.00303 -0.0663 0.8780 0.0212
-6.000 -0.2094 0.00853 0.00287 -0.0661 0.8688 0.0235
-5.750 -0.1817 0.00842 0.00272 -0.0659 0.8577 0.0252
-5.500 -0.1541 0.00834 0.00258 -0.0657 0.8451 0.0259
-5.250 -0.1268 0.00814 0.00231 -0.0654 0.8272 0.0279
-5.000 -0.1005 0.00804 0.00209 -0.0649 0.7878 0.0301
-4.750 -0.0746 0.00806 0.00191 -0.0643 0.7436 0.0318
-4.500 -0.0477 0.00806 0.00177 -0.0640 0.7175 0.0334
-4.250 -0.0202 0.00802 0.00164 -0.0638 0.7005 0.0346
-4.000 0.0076 0.00798 0.00152 -0.0637 0.6869 0.0355
-3.750 0.0354 0.00790 0.00140 -0.0636 0.6726 0.0403
-3.500 0.0631 0.00783 0.00131 -0.0635 0.6590 0.0479
-3.250 0.0909 0.00772 0.00125 -0.0634 0.6482 0.0690
-3.000 0.1192 0.00765 0.00119 -0.0634 0.6405 0.0797
-2.750 0.1473 0.00763 0.00114 -0.0634 0.6323 0.0853
-2.500 0.1755 0.00758 0.00109 -0.0634 0.6229 0.0922
-2.250 0.2036 0.00757 0.00104 -0.0634 0.6106 0.0978
-2.000 0.2315 0.00757 0.00100 -0.0633 0.5960 0.1027
-1.750 0.2595 0.00754 0.00096 -0.0633 0.5816 0.1122
-1.500 0.2870 0.00744 0.00093 -0.0633 0.5619 0.1569
-1.250 0.3144 0.00741 0.00094 -0.0632 0.5382 0.2039
-1.000 0.3415 0.00750 0.00095 -0.0631 0.5015 0.2216
-0.750 0.3677 0.00766 0.00099 -0.0629 0.4469 0.2572
-0.500 0.3939 0.00758 0.00106 -0.0629 0.4079 0.3650
-0.250 0.4205 0.00756 0.00114 -0.0628 0.3771 0.4501
0.000 0.4471 0.00753 0.00124 -0.0627 0.3492 0.5351
0.250 0.4733 0.00734 0.00133 -0.0626 0.3294 0.6645
0.500 0.4961 0.00691 0.00145 -0.0615 0.3164 0.8521
0.750 0.5214 0.00680 0.00153 -0.0606 0.3051 0.9712
1.000 0.5563 0.00692 0.00159 -0.0623 0.2933 1.0000
1.250 0.5836 0.00705 0.00167 -0.0622 0.2819 1.0000
1.500 0.6107 0.00720 0.00176 -0.0621 0.2689 1.0000
1.750 0.6378 0.00736 0.00186 -0.0620 0.2544 1.0000
2.000 0.6643 0.00759 0.00198 -0.0619 0.2316 1.0000
2.250 0.6903 0.00790 0.00213 -0.0617 0.1973 1.0000
2.500 0.7132 0.00864 0.00250 -0.0610 0.1195 1.0000
2.750 0.7398 0.00886 0.00268 -0.0609 0.1100 1.0000
3.000 0.7666 0.00906 0.00284 -0.0608 0.1032 1.0000
3.250 0.7935 0.00925 0.00302 -0.0607 0.0989 1.0000
3.500 0.8201 0.00946 0.00321 -0.0606 0.0942 1.0000
3.750 0.8470 0.00964 0.00340 -0.0606 0.0906 1.0000
4.000 0.8739 0.00981 0.00358 -0.0605 0.0884 1.0000
4.250 0.9006 0.01000 0.00378 -0.0604 0.0858 1.0000
4.500 0.9269 0.01024 0.00400 -0.0603 0.0809 1.0000
4.750 0.9533 0.01046 0.00422 -0.0602 0.0769 1.0000
5.000 0.9797 0.01066 0.00442 -0.0601 0.0724 1.0000
5.250 1.0055 0.01094 0.00466 -0.0600 0.0654 1.0000
5.500 1.0317 0.01117 0.00490 -0.0599 0.0613 1.0000
5.750 1.0571 0.01148 0.00516 -0.0597 0.0534 1.0000
6.000 1.0826 0.01178 0.00544 -0.0595 0.0472 1.0000
6.250 1.1070 0.01219 0.00580 -0.0592 0.0375 1.0000
6.500 1.1293 0.01286 0.00635 -0.0585 0.0200 1.0000
6.750 1.1524 0.01342 0.00688 -0.0580 0.0129 1.0000
7.000 1.1765 0.01384 0.00733 -0.0576 0.0110 1.0000
7.250 1.1998 0.01434 0.00784 -0.0571 0.0092 1.0000
7.500 1.2237 0.01475 0.00830 -0.0567 0.0084 1.0000
7.750 1.2470 0.01521 0.00879 -0.0562 0.0075 1.0000
8.000 1.2695 0.01574 0.00937 -0.0557 0.0067 1.0000
8.250 1.2917 0.01629 0.00996 -0.0551 0.0061 1.0000
8.500 1.3142 0.01678 0.01051 -0.0545 0.0058 1.0000
8.750 1.3361 0.01730 0.01109 -0.0539 0.0054 1.0000
9.000 1.3575 0.01786 0.01170 -0.0532 0.0051 1.0000
9.250 1.3781 0.01848 0.01237 -0.0524 0.0048 1.0000
9.500 1.3974 0.01921 0.01315 -0.0515 0.0045 1.0000
9.750 1.4156 0.02000 0.01404 -0.0503 0.0042 1.0000
10.000 1.4347 0.02065 0.01475 -0.0494 0.0041 1.0000
10.250 1.4530 0.02133 0.01551 -0.0483 0.0039 1.0000
10.500 1.4702 0.02206 0.01631 -0.0472 0.0037 1.0000
10.750 1.4865 0.02281 0.01714 -0.0459 0.0036 1.0000
11.000 1.5013 0.02361 0.01801 -0.0444 0.0034 1.0000
11.250 1.5124 0.02446 0.01893 -0.0423 0.0033 1.0000
11.500 1.5219 0.02539 0.01995 -0.0401 0.0032 1.0000
11.750 1.5301 0.02645 0.02110 -0.0379 0.0031 1.0000
12.000 1.5362 0.02771 0.02246 -0.0357 0.0030 1.0000
12.250 1.5399 0.02924 0.02409 -0.0336 0.0029 1.0000
12.500 1.5397 0.03119 0.02617 -0.0315 0.0028 1.0000
12.750 1.5440 0.03286 0.02796 -0.0301 0.0027 1.0000
13.000 1.5468 0.03480 0.03001 -0.0289 0.0027 1.0000
13.250 1.5481 0.03699 0.03231 -0.0280 0.0027 1.0000
13.500 1.5484 0.03947 0.03492 -0.0274 0.0026 1.0000
13.750 1.5462 0.04241 0.03799 -0.0273 0.0026 1.0000
14.000 1.5428 0.04573 0.04144 -0.0276 0.0026 1.0000
14.250 1.5373 0.04948 0.04532 -0.0283 0.0025 1.0000
14.500 1.5293 0.05372 0.04969 -0.0293 0.0025 1.0000
14.750 1.5192 0.05846 0.05458 -0.0307 0.0025 1.0000
15.000 1.5053 0.06391 0.06017 -0.0326 0.0025 1.0000
15.250 1.4889 0.07008 0.06650 -0.0350 0.0025 1.0000
15.500 1.4692 0.07720 0.07377 -0.0381 0.0025 1.0000
15.750 1.4471 0.08505 0.08177 -0.0417 0.0025 1.0000
16.000 1.4211 0.09388 0.09076 -0.0457 0.0025 1.0000
16.250 1.3930 0.10315 0.10018 -0.0500 0.0025 1.0000
16.500 1.3621 0.11315 0.11032 -0.0546 0.0025 1.0000
16.750 1.3318 0.12324 0.12055 -0.0593 0.0025 1.0000
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Polar data table (+)
Polar graphs
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