N-22 (n22-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: N-22 (n22-il) Reynolds number: 200,000 Max Cl/Cd: 71.69 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n22-il-200000.txt Download as CSV file: xf-n22-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3569 0.08899 0.08558 -0.0364 0.9999 0.0806
-10.000 -0.3844 0.08772 0.08442 -0.0334 0.9999 0.0819
-9.750 -0.4371 0.07700 0.07363 -0.0551 0.9914 0.0846
-9.500 -0.4129 0.07552 0.07228 -0.0499 0.9900 0.0857
-9.250 -0.3870 0.07366 0.07042 -0.0491 0.9867 0.0871
-9.000 -0.3588 0.07024 0.06696 -0.0533 0.9830 0.0897
-8.750 -0.3417 0.05780 0.05409 -0.0738 0.9714 0.0986
-8.500 -0.3381 0.03946 0.03463 -0.0837 0.9613 0.0742
-8.250 -0.3064 0.03449 0.02932 -0.0869 0.9575 0.0692
-8.000 -0.2720 0.02938 0.02354 -0.0905 0.9550 0.0679
-7.750 -0.2458 0.02691 0.02065 -0.0910 0.9464 0.0687
-7.500 -0.2082 0.02444 0.01775 -0.0934 0.9430 0.0693
-7.250 -0.1690 0.02257 0.01551 -0.0957 0.9403 0.0705
-7.000 -0.1404 0.02152 0.01418 -0.0957 0.9318 0.0720
-6.750 -0.1053 0.01998 0.01247 -0.0970 0.9271 0.0743
-6.500 -0.0685 0.01895 0.01141 -0.0986 0.9235 0.0768
-6.250 -0.0427 0.01828 0.01067 -0.0979 0.9134 0.0792
-6.000 -0.0089 0.01749 0.00976 -0.0985 0.9083 0.0825
-5.750 0.0169 0.01674 0.00897 -0.0978 0.8984 0.0864
-5.500 0.0476 0.01611 0.00837 -0.0979 0.8922 0.0917
-5.250 0.0736 0.01570 0.00786 -0.0970 0.8818 0.0971
-5.000 0.1021 0.01496 0.00720 -0.0967 0.8746 0.1054
-4.750 0.1275 0.01449 0.00676 -0.0958 0.8635 0.1166
-4.500 0.1543 0.01403 0.00634 -0.0952 0.8542 0.1331
-4.250 0.1816 0.01362 0.00594 -0.0947 0.8450 0.1578
-4.000 0.2077 0.01322 0.00568 -0.0942 0.8348 0.1870
-3.750 0.2353 0.01284 0.00537 -0.0938 0.8267 0.2212
-3.500 0.2611 0.01249 0.00522 -0.0933 0.8156 0.2652
-3.250 0.2873 0.01203 0.00507 -0.0929 0.8064 0.3461
-3.000 0.3115 0.01139 0.00498 -0.0921 0.7965 0.4998
-2.750 0.3311 0.01070 0.00503 -0.0899 0.7862 0.7057
-2.500 0.3780 0.01015 0.00491 -0.0919 0.7777 0.9742
-2.250 0.4172 0.01016 0.00479 -0.0942 0.7658 1.0001
-2.000 0.4428 0.01022 0.00470 -0.0936 0.7549 1.0001
-1.750 0.4691 0.01027 0.00457 -0.0930 0.7446 1.0001
-1.500 0.4945 0.01034 0.00454 -0.0924 0.7320 1.0001
-1.250 0.5204 0.01042 0.00451 -0.0919 0.7200 1.0001
-1.000 0.5468 0.01051 0.00446 -0.0914 0.7086 1.0001
-0.750 0.5732 0.01060 0.00443 -0.0909 0.6965 1.0001
-0.500 0.5992 0.01069 0.00444 -0.0904 0.6829 1.0001
-0.250 0.6253 0.01080 0.00446 -0.0900 0.6691 1.0001
0.000 0.6516 0.01091 0.00448 -0.0895 0.6553 1.0001
0.250 0.6778 0.01104 0.00451 -0.0891 0.6414 1.0001
0.500 0.7040 0.01118 0.00454 -0.0887 0.6267 1.0001
0.750 0.7300 0.01132 0.00459 -0.0883 0.6113 1.0001
1.000 0.7559 0.01149 0.00467 -0.0878 0.5954 1.0001
1.250 0.7817 0.01168 0.00476 -0.0874 0.5796 1.0001
1.500 0.8074 0.01189 0.00487 -0.0870 0.5637 1.0001
1.750 0.8330 0.01213 0.00502 -0.0866 0.5478 1.0001
2.000 0.8585 0.01238 0.00518 -0.0862 0.5324 1.0001
2.250 0.8840 0.01266 0.00536 -0.0858 0.5178 1.0001
2.500 0.9092 0.01293 0.00557 -0.0854 0.5028 1.0001
2.750 0.9340 0.01321 0.00577 -0.0850 0.4872 1.0001
3.000 0.9585 0.01350 0.00598 -0.0845 0.4718 1.0001
3.250 0.9832 0.01379 0.00624 -0.0840 0.4579 1.0001
3.500 1.0081 0.01411 0.00651 -0.0837 0.4457 1.0001
3.750 1.0330 0.01446 0.00678 -0.0833 0.4349 1.0001
4.000 1.0577 0.01477 0.00708 -0.0829 0.4240 1.0001
4.250 1.0824 0.01510 0.00742 -0.0826 0.4138 1.0001
4.750 1.1313 0.01578 0.00809 -0.0819 0.3945 1.0001
5.000 1.1554 0.01616 0.00845 -0.0815 0.3853 1.0001
5.250 1.1791 0.01650 0.00880 -0.0810 0.3754 1.0001
5.500 1.2025 0.01686 0.00920 -0.0805 0.3657 1.0001
5.750 1.2259 0.01729 0.00957 -0.0800 0.3567 1.0001
6.000 1.2481 0.01760 0.01000 -0.0793 0.3464 1.0001
6.250 1.2702 0.01801 0.01042 -0.0786 0.3366 1.0001
6.500 1.2913 0.01842 0.01083 -0.0778 0.3259 1.0001
6.750 1.3114 0.01879 0.01129 -0.0768 0.3138 1.0001
7.000 1.3306 0.01922 0.01177 -0.0757 0.3013 1.0001
7.250 1.3486 0.01970 0.01226 -0.0744 0.2881 1.0001
7.500 1.3649 0.02021 0.01280 -0.0728 0.2735 1.0001
7.750 1.3794 0.02077 0.01337 -0.0710 0.2575 1.0001
8.000 1.3917 0.02139 0.01398 -0.0689 0.2411 1.0001
8.250 1.4012 0.02210 0.01466 -0.0664 0.2259 1.0001
8.500 1.4107 0.02293 0.01546 -0.0641 0.2122 1.0001
8.750 1.4197 0.02386 0.01636 -0.0618 0.2001 1.0001
9.000 1.4278 0.02491 0.01736 -0.0597 0.1895 1.0001
9.250 1.4387 0.02588 0.01839 -0.0580 0.1799 1.0001
9.500 1.4470 0.02705 0.01955 -0.0561 0.1722 1.0001
9.750 1.4566 0.02818 0.02073 -0.0545 0.1646 1.0001
10.000 1.4645 0.02946 0.02203 -0.0529 0.1579 1.0001
10.250 1.4732 0.03070 0.02335 -0.0515 0.1508 1.0001
10.500 1.4796 0.03218 0.02484 -0.0500 0.1447 1.0001
10.750 1.4884 0.03351 0.02630 -0.0489 0.1383 1.0001
11.000 1.4919 0.03530 0.02808 -0.0476 0.1326 1.0001
11.250 1.5007 0.03673 0.02972 -0.0468 0.1258 1.0001
11.500 1.5018 0.03887 0.03185 -0.0457 0.1195 1.0001
11.750 1.5085 0.04065 0.03381 -0.0452 0.1107 1.0001
12.000 1.5098 0.04301 0.03625 -0.0446 0.1000 1.0001
12.250 1.5060 0.04604 0.03929 -0.0442 0.0853 1.0001
12.500 1.4966 0.04978 0.04300 -0.0437 0.0672 1.0001
12.750 1.4835 0.05411 0.04727 -0.0435 0.0557 1.0001
13.000 1.4708 0.05859 0.05176 -0.0435 0.0494 1.0001
13.250 1.4569 0.06342 0.05663 -0.0439 0.0460 1.0001
13.500 1.4462 0.06804 0.06137 -0.0444 0.0433 1.0001
13.750 1.4337 0.07303 0.06645 -0.0452 0.0415 1.0001
14.000 1.4191 0.07848 0.07198 -0.0464 0.0402 1.0001
14.250 1.4067 0.08372 0.07732 -0.0475 0.0390 1.0001
14.500 1.3973 0.08860 0.08233 -0.0487 0.0379 1.0001
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Polar data table (+)
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