N-10 (n10-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: N-10 (n10-il) Reynolds number: 100,000 Max Cl/Cd: 52.62 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n10-il-100000-n5.txt Download as CSV file: xf-n10-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: N-10
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.3956 0.09320 0.08811 -0.0409 0.9999 0.0442
-10.750 -0.4002 0.08934 0.08431 -0.0418 0.9999 0.0440
-10.500 -0.4088 0.08544 0.08050 -0.0426 0.9999 0.0440
-10.250 -0.4234 0.08159 0.07675 -0.0431 0.9999 0.0441
-10.000 -0.4411 0.07753 0.07280 -0.0440 0.9999 0.0441
-9.750 -0.4574 0.07238 0.06771 -0.0463 0.9999 0.0442
-9.500 -0.4747 0.06649 0.06180 -0.0484 0.9999 0.0443
-9.250 -0.4911 0.06025 0.05545 -0.0496 0.9999 0.0445
-9.000 -0.4840 0.05056 0.04516 -0.0572 0.9937 0.0449
-8.750 -0.4646 0.04399 0.03799 -0.0620 0.9868 0.0457
-8.500 -0.4368 0.04218 0.03614 -0.0640 0.9816 0.0473
-8.250 -0.4080 0.03983 0.03356 -0.0663 0.9760 0.0492
-8.000 -0.3818 0.03613 0.02935 -0.0685 0.9696 0.0504
-7.750 -0.3525 0.03288 0.02554 -0.0705 0.9642 0.0515
-7.500 -0.3229 0.03050 0.02262 -0.0719 0.9584 0.0535
-7.250 -0.2917 0.02852 0.02009 -0.0731 0.9524 0.0553
-7.000 -0.2567 0.02661 0.01783 -0.0749 0.9487 0.0563
-6.750 -0.2285 0.02525 0.01633 -0.0753 0.9412 0.0575
-6.500 -0.1941 0.02407 0.01501 -0.0768 0.9366 0.0590
-6.250 -0.1600 0.02314 0.01394 -0.0782 0.9319 0.0614
-6.000 -0.1297 0.02235 0.01299 -0.0787 0.9247 0.0645
-5.750 -0.0942 0.02144 0.01191 -0.0801 0.9202 0.0668
-5.500 -0.0642 0.02057 0.01100 -0.0805 0.9127 0.0689
-5.250 -0.0303 0.01979 0.01023 -0.0816 0.9061 0.0721
-5.000 0.0012 0.01915 0.00953 -0.0821 0.8976 0.0763
-4.750 0.0359 0.01845 0.00879 -0.0832 0.8897 0.0830
-4.500 0.0661 0.01791 0.00821 -0.0834 0.8788 0.0934
-4.250 0.0981 0.01724 0.00754 -0.0840 0.8691 0.1088
-4.000 0.1296 0.01655 0.00704 -0.0845 0.8595 0.1378
-3.750 0.1582 0.01607 0.00681 -0.0845 0.8481 0.2076
-3.500 0.1875 0.01560 0.00653 -0.0847 0.8371 0.2755
-3.250 0.2167 0.01496 0.00631 -0.0848 0.8261 0.3797
-3.000 0.2421 0.01432 0.00618 -0.0840 0.8137 0.5292
-2.750 0.2625 0.01361 0.00619 -0.0814 0.8017 0.7343
-2.500 0.3163 0.01325 0.00604 -0.0853 0.7920 0.9652
-2.250 0.3563 0.01321 0.00579 -0.0876 0.7809 1.0001
-2.000 0.3811 0.01327 0.00569 -0.0869 0.7677 1.0001
-1.750 0.4063 0.01333 0.00560 -0.0863 0.7547 1.0001
-1.500 0.4318 0.01339 0.00552 -0.0857 0.7417 1.0001
-1.250 0.4575 0.01345 0.00546 -0.0851 0.7284 1.0001
-1.000 0.4831 0.01352 0.00540 -0.0845 0.7142 1.0001
-0.750 0.5088 0.01359 0.00535 -0.0839 0.6993 1.0001
-0.500 0.5345 0.01367 0.00530 -0.0833 0.6836 1.0001
-0.250 0.5603 0.01377 0.00527 -0.0827 0.6675 1.0001
0.000 0.5861 0.01388 0.00526 -0.0821 0.6510 1.0001
0.250 0.6117 0.01403 0.00529 -0.0816 0.6342 1.0001
0.500 0.6372 0.01420 0.00534 -0.0810 0.6167 1.0001
0.750 0.6624 0.01439 0.00542 -0.0804 0.5983 1.0001
1.000 0.6871 0.01461 0.00554 -0.0797 0.5783 1.0001
1.250 0.7115 0.01483 0.00569 -0.0790 0.5561 1.0001
1.500 0.7357 0.01508 0.00583 -0.0783 0.5337 1.0001
1.750 0.7599 0.01534 0.00601 -0.0777 0.5111 1.0001
2.000 0.7841 0.01563 0.00619 -0.0770 0.4915 1.0001
2.250 0.8082 0.01595 0.00639 -0.0764 0.4742 1.0001
2.500 0.8321 0.01630 0.00663 -0.0757 0.4585 1.0001
2.750 0.8560 0.01668 0.00690 -0.0751 0.4436 1.0001
3.000 0.8797 0.01707 0.00720 -0.0745 0.4296 1.0001
3.250 0.9036 0.01747 0.00755 -0.0740 0.4170 1.0001
3.500 0.9277 0.01788 0.00791 -0.0735 0.4065 1.0001
3.750 0.9520 0.01829 0.00829 -0.0731 0.3981 1.0001
4.000 0.9766 0.01868 0.00873 -0.0727 0.3899 1.0001
4.250 1.0006 0.01913 0.00914 -0.0722 0.3816 1.0001
4.500 1.0244 0.01952 0.00960 -0.0717 0.3722 1.0001
4.750 1.0480 0.01997 0.01003 -0.0712 0.3638 1.0001
5.000 1.0714 0.02037 0.01055 -0.0707 0.3551 1.0001
5.250 1.0950 0.02083 0.01103 -0.0703 0.3478 1.0001
5.500 1.1181 0.02125 0.01158 -0.0697 0.3398 1.0001
5.750 1.1411 0.02173 0.01208 -0.0692 0.3326 1.0001
6.000 1.1634 0.02216 0.01270 -0.0685 0.3238 1.0001
6.250 1.1852 0.02264 0.01325 -0.0678 0.3157 1.0001
6.500 1.2062 0.02310 0.01387 -0.0669 0.3058 1.0001
6.750 1.2264 0.02358 0.01449 -0.0660 0.2954 1.0001
7.000 1.2451 0.02407 0.01512 -0.0648 0.2833 1.0001
7.250 1.2622 0.02456 0.01574 -0.0633 0.2681 1.0001
7.500 1.2778 0.02507 0.01637 -0.0617 0.2491 1.0001
7.750 1.2909 0.02569 0.01700 -0.0598 0.2277 1.0001
8.000 1.3029 0.02643 0.01774 -0.0578 0.2049 1.0001
8.250 1.3105 0.02737 0.01860 -0.0553 0.1874 1.0001
8.500 1.3163 0.02849 0.01965 -0.0526 0.1727 1.0001
9.000 1.3271 0.03113 0.02226 -0.0479 0.1472 1.0001
9.250 1.3330 0.03252 0.02371 -0.0458 0.1358 1.0001
9.500 1.3376 0.03406 0.02532 -0.0439 0.1238 1.0001
9.750 1.3412 0.03574 0.02706 -0.0421 0.1122 1.0001
10.000 1.3452 0.03749 0.02891 -0.0406 0.0983 1.0001
10.250 1.3475 0.03950 0.03100 -0.0392 0.0734 1.0001
10.500 1.3380 0.04264 0.03397 -0.0376 0.0543 1.0001
10.750 1.3282 0.04605 0.03734 -0.0364 0.0446 1.0001
11.000 1.3194 0.04957 0.04094 -0.0355 0.0390 1.0001
11.250 1.3105 0.05332 0.04479 -0.0351 0.0357 1.0001
11.500 1.3017 0.05728 0.04889 -0.0351 0.0334 1.0001
11.750 1.2911 0.06166 0.05341 -0.0355 0.0317 1.0001
12.000 1.2786 0.06650 0.05837 -0.0362 0.0306 1.0001
12.250 1.2679 0.07132 0.06335 -0.0372 0.0296 1.0001
12.500 1.2568 0.07640 0.06861 -0.0385 0.0287 1.0001
12.750 1.2451 0.08179 0.07415 -0.0401 0.0279 1.0001
13.000 1.2332 0.08739 0.07991 -0.0419 0.0272 1.0001
13.250 1.2214 0.09312 0.08578 -0.0438 0.0266 1.0001
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Polar data table (+)
Polar graphs
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