N-22 (n22-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: N-22 (n22-il) Reynolds number: 200,000 Max Cl/Cd: 70.73 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n22-il-200000-n5.txt Download as CSV file: xf-n22-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: N-22
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.3934 0.08863 0.08487 -0.0452 0.9999 0.0353
-11.500 -0.4017 0.08416 0.08045 -0.0469 0.9999 0.0356
-11.250 -0.4159 0.07984 0.07620 -0.0479 0.9999 0.0361
-11.000 -0.5367 0.04288 0.03862 -0.0826 0.9820 0.0369
-10.750 -0.5320 0.03435 0.02917 -0.0882 0.9734 0.0380
-10.500 -0.5126 0.03044 0.02458 -0.0901 0.9669 0.0389
-10.250 -0.4866 0.02819 0.02198 -0.0914 0.9616 0.0398
-10.000 -0.4553 0.02696 0.02066 -0.0929 0.9582 0.0406
-9.750 -0.4303 0.02583 0.01939 -0.0930 0.9505 0.0413
-9.500 -0.4008 0.02451 0.01785 -0.0939 0.9455 0.0421
-9.250 -0.3740 0.02332 0.01644 -0.0941 0.9387 0.0429
-9.000 -0.3462 0.02218 0.01509 -0.0943 0.9319 0.0438
-8.750 -0.3169 0.02120 0.01389 -0.0947 0.9264 0.0450
-8.500 -0.2908 0.02038 0.01286 -0.0944 0.9176 0.0460
-8.250 -0.2617 0.01944 0.01177 -0.0946 0.9119 0.0470
-8.000 -0.2363 0.01866 0.01095 -0.0942 0.9025 0.0478
-7.750 -0.2078 0.01798 0.01022 -0.0942 0.8959 0.0489
-7.500 -0.1816 0.01742 0.00959 -0.0937 0.8863 0.0500
-7.250 -0.1535 0.01684 0.00892 -0.0936 0.8792 0.0513
-7.000 -0.1270 0.01635 0.00835 -0.0931 0.8694 0.0529
-6.750 -0.0994 0.01591 0.00779 -0.0928 0.8612 0.0547
-6.500 -0.0729 0.01535 0.00722 -0.0924 0.8516 0.0567
-6.250 -0.0458 0.01494 0.00678 -0.0921 0.8423 0.0587
-6.000 -0.0184 0.01457 0.00633 -0.0918 0.8332 0.0612
-5.750 0.0087 0.01425 0.00593 -0.0914 0.8227 0.0640
-5.500 0.0359 0.01388 0.00554 -0.0911 0.8130 0.0677
-5.250 0.0632 0.01362 0.00524 -0.0907 0.8023 0.0730
-5.000 0.0904 0.01336 0.00496 -0.0904 0.7912 0.0795
-4.750 0.1179 0.01314 0.00469 -0.0901 0.7801 0.0882
-4.500 0.1452 0.01293 0.00446 -0.0898 0.7687 0.1002
-4.250 0.1726 0.01275 0.00429 -0.0896 0.7576 0.1158
-4.000 0.2002 0.01258 0.00413 -0.0894 0.7475 0.1334
-3.750 0.2277 0.01242 0.00400 -0.0892 0.7372 0.1532
-3.500 0.2552 0.01228 0.00388 -0.0890 0.7273 0.1749
-3.000 0.3101 0.01197 0.00370 -0.0887 0.7070 0.2352
-2.750 0.3372 0.01176 0.00364 -0.0886 0.6969 0.2866
-2.500 0.3636 0.01147 0.00361 -0.0884 0.6865 0.3733
-2.250 0.3892 0.01110 0.00362 -0.0880 0.6759 0.4889
-2.000 0.4136 0.01074 0.00364 -0.0872 0.6654 0.6134
-1.750 0.4359 0.01039 0.00367 -0.0855 0.6542 0.7442
-1.500 0.4685 0.01012 0.00370 -0.0856 0.6420 0.9174
-1.250 0.5127 0.01014 0.00363 -0.0890 0.6293 1.0001
-1.000 0.5389 0.01025 0.00362 -0.0886 0.6169 1.0001
-0.500 0.5913 0.01050 0.00364 -0.0878 0.5896 1.0001
-0.250 0.6175 0.01064 0.00367 -0.0875 0.5756 1.0001
0.000 0.6437 0.01079 0.00372 -0.0871 0.5619 1.0001
0.250 0.6697 0.01096 0.00379 -0.0868 0.5476 1.0001
0.500 0.6956 0.01114 0.00387 -0.0864 0.5327 1.0001
0.750 0.7214 0.01134 0.00397 -0.0861 0.5180 1.0001
1.000 0.7471 0.01155 0.00408 -0.0857 0.5039 1.0001
1.250 0.7727 0.01178 0.00421 -0.0854 0.4906 1.0001
1.500 0.7983 0.01200 0.00436 -0.0850 0.4769 1.0001
1.750 0.8239 0.01224 0.00453 -0.0847 0.4637 1.0001
2.000 0.8493 0.01248 0.00471 -0.0844 0.4515 1.0001
2.250 0.8746 0.01275 0.00491 -0.0840 0.4405 1.0001
2.500 0.8998 0.01302 0.00513 -0.0837 0.4288 1.0001
2.750 0.9245 0.01330 0.00535 -0.0833 0.4152 1.0001
3.000 0.9487 0.01361 0.00558 -0.0828 0.4003 1.0001
3.250 0.9728 0.01393 0.00583 -0.0823 0.3864 1.0001
3.500 0.9970 0.01424 0.00610 -0.0819 0.3755 1.0001
3.750 1.0214 0.01455 0.00637 -0.0815 0.3654 1.0001
4.000 1.0459 0.01484 0.00667 -0.0811 0.3564 1.0001
4.250 1.0698 0.01518 0.00697 -0.0807 0.3476 1.0001
4.500 1.0942 0.01547 0.00729 -0.0803 0.3391 1.0001
4.750 1.1174 0.01583 0.00763 -0.0798 0.3308 1.0001
5.000 1.1413 0.01614 0.00797 -0.0794 0.3219 1.0001
5.250 1.1639 0.01652 0.00834 -0.0788 0.3134 1.0001
5.500 1.1873 0.01684 0.00872 -0.0783 0.3045 1.0001
5.750 1.2094 0.01723 0.00911 -0.0776 0.2963 1.0001
6.000 1.2317 0.01759 0.00952 -0.0770 0.2870 1.0001
6.250 1.2532 0.01799 0.00994 -0.0763 0.2778 1.0001
6.500 1.2733 0.01844 0.01041 -0.0753 0.2673 1.0001
6.750 1.2936 0.01886 0.01087 -0.0745 0.2553 1.0001
7.000 1.3126 0.01935 0.01137 -0.0734 0.2426 1.0001
7.250 1.3301 0.01989 0.01192 -0.0721 0.2293 1.0001
7.500 1.3457 0.02048 0.01252 -0.0705 0.2162 1.0001
7.750 1.3585 0.02115 0.01317 -0.0686 0.2026 1.0001
8.000 1.3702 0.02193 0.01392 -0.0665 0.1891 1.0001
8.250 1.3808 0.02282 0.01478 -0.0645 0.1769 1.0001
8.500 1.3908 0.02379 0.01573 -0.0625 0.1659 1.0001
8.750 1.4021 0.02474 0.01669 -0.0609 0.1566 1.0001
9.000 1.4115 0.02582 0.01779 -0.0591 0.1487 1.0001
9.250 1.4219 0.02690 0.01889 -0.0575 0.1407 1.0001
9.500 1.4310 0.02808 0.02010 -0.0560 0.1337 1.0001
9.750 1.4406 0.02928 0.02136 -0.0546 0.1271 1.0001
10.000 1.4485 0.03064 0.02276 -0.0532 0.1215 1.0001
10.250 1.4583 0.03191 0.02411 -0.0521 0.1155 1.0001
10.500 1.4636 0.03357 0.02580 -0.0508 0.1100 1.0001
10.750 1.4731 0.03496 0.02729 -0.0499 0.1038 1.0001
11.000 1.4771 0.03686 0.02922 -0.0488 0.0975 1.0001
11.250 1.4842 0.03856 0.03101 -0.0481 0.0903 1.0001
11.500 1.4874 0.04066 0.03316 -0.0473 0.0834 1.0001
11.750 1.4896 0.04294 0.03548 -0.0466 0.0746 1.0001
12.000 1.4894 0.04553 0.03810 -0.0459 0.0630 1.0001
12.250 1.4821 0.04895 0.04147 -0.0454 0.0478 1.0001
12.500 1.4708 0.05295 0.04544 -0.0450 0.0383 1.0001
12.750 1.4607 0.05703 0.04955 -0.0449 0.0331 1.0001
13.000 1.4519 0.06111 0.05371 -0.0450 0.0299 1.0001
13.250 1.4429 0.06540 0.05810 -0.0454 0.0278 1.0001
13.500 1.4351 0.06967 0.06251 -0.0460 0.0261 1.0001
13.750 1.4254 0.07433 0.06729 -0.0469 0.0248 1.0001
14.000 1.4143 0.07934 0.07241 -0.0480 0.0239 1.0001
14.250 1.4045 0.08431 0.07752 -0.0492 0.0231 1.0001
14.500 1.3949 0.08934 0.08270 -0.0506 0.0224 1.0001
14.750 1.3841 0.09464 0.08815 -0.0522 0.0218 1.0001
15.000 1.3727 0.10016 0.09381 -0.0540 0.0213 1.0001
15.250 1.3606 0.10589 0.09967 -0.0559 0.0208 1.0001
15.500 1.3478 0.11182 0.10574 -0.0581 0.0205 1.0001
15.750 1.3346 0.11791 0.11196 -0.0604 0.0201 1.0001
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Polar data table (+)
Polar graphs
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