N-9 (n9-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: N-9 (n9-il) Reynolds number: 50,000 Max Cl/Cd: 36.76 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n9-il-50000.txt Download as CSV file: xf-n9-il-50000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4715 0.11058 0.10359 -0.0053 1.0000 0.2159
-9.750 -0.4607 0.10620 0.09922 -0.0050 1.0000 0.2233
-9.500 -0.4762 0.10516 0.09834 -0.0074 1.0000 0.2320
-9.250 -0.4565 0.10011 0.09325 -0.0057 1.0000 0.2437
-9.000 -0.4515 0.09658 0.08978 -0.0056 1.0000 0.2539
-8.500 -0.4481 0.09056 0.08391 -0.0048 1.0000 0.2827
-8.250 -0.4438 0.08758 0.08099 -0.0036 1.0000 0.3011
-8.000 -0.4467 0.08511 0.07862 -0.0033 1.0000 0.3201
-7.750 -0.4468 0.08214 0.07575 -0.0028 1.0000 0.3393
-7.500 -0.4324 0.07860 0.07223 0.0000 1.0000 0.3615
-7.250 -0.4329 0.07589 0.06961 0.0012 1.0000 0.3854
-7.000 -0.4322 0.07344 0.06723 0.0033 1.0000 0.4138
-6.750 -0.4129 0.06998 0.06377 0.0082 1.0000 0.4508
-6.500 -0.4047 0.06725 0.06110 0.0126 1.0000 0.4929
-6.000 -0.3607 0.04497 0.03722 -0.0403 1.0000 0.1758
-5.750 -0.3348 0.03995 0.03135 -0.0423 1.0000 0.1585
-5.500 -0.3128 0.03661 0.02771 -0.0420 1.0000 0.1556
-5.250 -0.2888 0.03379 0.02429 -0.0420 1.0000 0.1580
-5.000 -0.2641 0.03121 0.02123 -0.0416 1.0000 0.1600
-4.750 -0.2402 0.02909 0.01893 -0.0410 1.0000 0.1636
-4.500 -0.2149 0.02753 0.01690 -0.0404 1.0000 0.1735
-4.250 -0.1907 0.02596 0.01527 -0.0397 1.0000 0.1833
-4.000 -0.1651 0.02455 0.01369 -0.0391 1.0000 0.1960
-3.750 -0.1400 0.02340 0.01245 -0.0384 1.0000 0.2197
-3.500 -0.1139 0.02213 0.01126 -0.0378 1.0000 0.2527
-3.250 -0.0868 0.02082 0.01024 -0.0376 1.0000 0.3201
-3.000 -0.0590 0.01701 0.00923 -0.0346 1.0000 1.0000
-2.750 -0.0362 0.01723 0.00876 -0.0341 1.0000 1.0000
-2.500 -0.0153 0.01749 0.00863 -0.0334 1.0000 1.0000
-2.250 0.0053 0.01780 0.00863 -0.0329 1.0000 1.0000
-2.000 0.0256 0.01817 0.00872 -0.0324 1.0000 1.0000
-1.750 0.0459 0.01857 0.00890 -0.0321 1.0000 1.0000
-1.500 0.0661 0.01902 0.00916 -0.0318 1.0000 1.0000
-1.250 0.0863 0.01951 0.00948 -0.0315 1.0000 1.0000
-1.000 0.1063 0.02005 0.00986 -0.0314 1.0000 1.0000
-0.750 0.1263 0.02063 0.01032 -0.0313 1.0000 1.0000
-0.500 0.1461 0.02126 0.01085 -0.0313 1.0000 1.0000
-0.250 0.1657 0.02194 0.01146 -0.0313 1.0000 1.0000
0.000 0.1850 0.02269 0.01214 -0.0315 1.0000 1.0000
0.250 0.2443 0.02373 0.01312 -0.0390 0.9832 1.0000
0.500 0.3005 0.02454 0.01394 -0.0456 0.9625 1.0000
0.750 0.3570 0.02524 0.01466 -0.0519 0.9415 1.0000
1.000 0.4135 0.02575 0.01526 -0.0577 0.9192 1.0000
1.250 0.4645 0.02617 0.01578 -0.0622 0.8953 1.0000
1.500 0.5253 0.02625 0.01602 -0.0677 0.8726 1.0000
1.750 0.5691 0.02637 0.01630 -0.0699 0.8466 1.0000
2.000 0.6087 0.02642 0.01649 -0.0710 0.8200 1.0000
2.250 0.6472 0.02633 0.01654 -0.0715 0.7942 1.0000
2.500 0.6857 0.02591 0.01627 -0.0712 0.7683 1.0000
2.750 0.7215 0.02525 0.01569 -0.0698 0.7413 1.0000
3.000 0.7521 0.02480 0.01527 -0.0677 0.7127 1.0000
3.250 0.7785 0.02466 0.01518 -0.0654 0.6830 1.0000
3.500 0.8032 0.02466 0.01519 -0.0630 0.6530 1.0000
3.750 0.8259 0.02468 0.01523 -0.0605 0.6209 1.0000
4.000 0.8488 0.02478 0.01541 -0.0583 0.5903 1.0000
4.250 0.8712 0.02490 0.01559 -0.0561 0.5582 1.0000
4.500 0.8935 0.02478 0.01543 -0.0536 0.5207 1.0000
4.750 0.9130 0.02484 0.01537 -0.0506 0.4726 1.0000
5.000 0.9307 0.02557 0.01575 -0.0475 0.4078 1.0000
5.250 0.9489 0.02718 0.01684 -0.0450 0.3457 1.0000
5.500 0.9699 0.02891 0.01840 -0.0436 0.3070 1.0000
5.750 0.9930 0.03052 0.01993 -0.0426 0.2815 1.0000
6.000 1.0147 0.03202 0.02153 -0.0415 0.2599 1.0000
6.250 1.0380 0.03370 0.02332 -0.0407 0.2434 1.0000
6.500 1.0605 0.03527 0.02489 -0.0397 0.2270 1.0000
6.750 1.0824 0.03717 0.02691 -0.0388 0.2125 1.0000
7.000 1.1012 0.03914 0.02908 -0.0375 0.1971 1.0000
7.250 1.1184 0.04145 0.03162 -0.0360 0.1822 1.0000
7.500 1.1325 0.04389 0.03435 -0.0343 0.1665 1.0000
7.750 1.1451 0.04671 0.03740 -0.0326 0.1521 1.0000
8.000 1.1565 0.05005 0.04093 -0.0309 0.1401 1.0000
8.250 1.1730 0.05392 0.04475 -0.0299 0.1295 1.0000
8.500 1.1635 0.05838 0.05003 -0.0268 0.1263 1.0000
8.750 1.1539 0.06302 0.05520 -0.0244 0.1232 1.0000
9.000 1.1439 0.06762 0.06014 -0.0225 0.1207 1.0000
9.250 1.1216 0.07295 0.06582 -0.0207 0.1212 1.0000
9.500 1.0879 0.07870 0.07182 -0.0194 0.1242 1.0000
9.750 1.0591 0.08490 0.07814 -0.0200 0.1266 1.0000
10.000 1.0357 0.09177 0.08507 -0.0222 0.1283 1.0000
10.250 1.0177 0.09911 0.09244 -0.0249 0.1294 1.0000
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Polar data table (+)
Polar graphs
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