N-22 (n22-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: N-22 (n22-il) Reynolds number: 500,000 Max Cl/Cd: 98.4 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n22-il-500000.txt Download as CSV file: xf-n22-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.2706 0.09637 0.09417 -0.0413 0.9999 0.0410
-12.000 -0.5603 0.05974 0.05745 -0.0628 0.9999 0.0336
-11.750 -0.6368 0.03767 0.03440 -0.0833 0.9915 0.0331
-11.500 -0.6267 0.03096 0.02700 -0.0876 0.9860 0.0339
-11.250 -0.5961 0.02921 0.02516 -0.0897 0.9840 0.0346
-11.000 -0.5624 0.02807 0.02396 -0.0919 0.9825 0.0352
-10.750 -0.5344 0.02666 0.02241 -0.0930 0.9781 0.0359
-10.500 -0.5035 0.02505 0.02058 -0.0947 0.9750 0.0369
-10.250 -0.4725 0.02324 0.01846 -0.0963 0.9720 0.0379
-10.000 -0.4405 0.02168 0.01661 -0.0977 0.9694 0.0386
-9.750 -0.4151 0.02079 0.01549 -0.0974 0.9621 0.0390
-9.500 -0.3888 0.01866 0.01316 -0.0978 0.9571 0.0400
-9.250 -0.3629 0.01787 0.01233 -0.0975 0.9504 0.0408
-9.000 -0.3369 0.01719 0.01158 -0.0970 0.9431 0.0416
-8.750 -0.3113 0.01652 0.01081 -0.0964 0.9359 0.0423
-8.500 -0.2863 0.01586 0.01005 -0.0956 0.9275 0.0431
-8.250 -0.2608 0.01525 0.00934 -0.0949 0.9195 0.0440
-8.000 -0.2352 0.01474 0.00872 -0.0941 0.9106 0.0449
-7.750 -0.2088 0.01439 0.00826 -0.0935 0.9016 0.0456
-7.500 -0.1840 0.01340 0.00718 -0.0928 0.8927 0.0467
-7.250 -0.1580 0.01282 0.00657 -0.0922 0.8825 0.0479
-7.000 -0.1315 0.01242 0.00612 -0.0917 0.8733 0.0491
-6.750 -0.1047 0.01207 0.00571 -0.0912 0.8626 0.0505
-6.500 -0.0776 0.01175 0.00532 -0.0908 0.8521 0.0519
-6.250 -0.0502 0.01153 0.00500 -0.0903 0.8419 0.0533
-6.000 -0.0239 0.01098 0.00442 -0.0899 0.8299 0.0559
-5.750 0.0035 0.01071 0.00411 -0.0896 0.8183 0.0583
-5.500 0.0311 0.01050 0.00383 -0.0893 0.8080 0.0611
-5.250 0.0587 0.01021 0.00349 -0.0891 0.7976 0.0648
-5.000 0.0866 0.01000 0.00327 -0.0889 0.7878 0.0701
-4.750 0.1144 0.00980 0.00304 -0.0887 0.7784 0.0778
-4.500 0.1426 0.00959 0.00287 -0.0886 0.7687 0.0899
-4.250 0.1706 0.00943 0.00273 -0.0885 0.7597 0.1087
-4.000 0.1987 0.00928 0.00263 -0.0884 0.7498 0.1300
-3.750 0.2268 0.00916 0.00254 -0.0884 0.7406 0.1509
-3.500 0.2550 0.00906 0.00246 -0.0883 0.7313 0.1723
-3.250 0.2831 0.00893 0.00240 -0.0883 0.7218 0.1983
-3.000 0.3109 0.00879 0.00233 -0.0883 0.7124 0.2361
-2.750 0.3388 0.00857 0.00230 -0.0883 0.7021 0.2967
-2.500 0.3661 0.00830 0.00228 -0.0883 0.6928 0.3877
-2.250 0.3929 0.00795 0.00228 -0.0882 0.6828 0.5095
-2.000 0.4184 0.00754 0.00233 -0.0877 0.6727 0.6575
-1.750 0.4383 0.00704 0.00240 -0.0855 0.6625 0.8449
-1.500 0.4834 0.00690 0.00240 -0.0886 0.6501 0.9901
-1.250 0.5181 0.00697 0.00238 -0.0901 0.6382 1.0001
-1.000 0.5445 0.00706 0.00237 -0.0897 0.6265 1.0001
-0.750 0.5709 0.00717 0.00238 -0.0893 0.6138 1.0001
-0.500 0.5975 0.00727 0.00240 -0.0891 0.5998 1.0001
-0.250 0.6241 0.00738 0.00243 -0.0888 0.5851 1.0001
0.000 0.6507 0.00751 0.00247 -0.0885 0.5701 1.0001
0.250 0.6773 0.00765 0.00253 -0.0883 0.5549 1.0001
0.500 0.7038 0.00781 0.00259 -0.0880 0.5391 1.0001
0.750 0.7302 0.00799 0.00268 -0.0878 0.5225 1.0001
1.000 0.7564 0.00818 0.00277 -0.0875 0.5056 1.0001
1.250 0.7827 0.00838 0.00289 -0.0873 0.4895 1.0001
1.500 0.8089 0.00859 0.00301 -0.0871 0.4735 1.0001
1.750 0.8346 0.00883 0.00315 -0.0868 0.4556 1.0001
2.250 0.8857 0.00935 0.00345 -0.0862 0.4203 1.0001
2.500 0.9118 0.00956 0.00362 -0.0860 0.4073 1.0001
2.750 0.9380 0.00978 0.00379 -0.0859 0.3961 1.0001
3.000 0.9639 0.01002 0.00397 -0.0857 0.3862 1.0001
3.250 0.9899 0.01024 0.00417 -0.0855 0.3765 1.0001
3.500 1.0159 0.01046 0.00436 -0.0854 0.3676 1.0001
3.750 1.0414 0.01071 0.00457 -0.0852 0.3585 1.0001
4.000 1.0675 0.01092 0.00478 -0.0850 0.3508 1.0001
4.250 1.0928 0.01118 0.00501 -0.0848 0.3429 1.0001
4.500 1.1186 0.01139 0.00523 -0.0847 0.3357 1.0001
4.750 1.1437 0.01165 0.00547 -0.0844 0.3279 1.0001
5.000 1.1690 0.01188 0.00572 -0.0842 0.3204 1.0001
5.250 1.1937 0.01215 0.00597 -0.0839 0.3118 1.0001
5.500 1.2187 0.01239 0.00623 -0.0837 0.3036 1.0001
5.750 1.2426 0.01270 0.00651 -0.0833 0.2949 1.0001
6.000 1.2673 0.01294 0.00678 -0.0831 0.2852 1.0001
6.250 1.2906 0.01325 0.00707 -0.0826 0.2732 1.0001
6.500 1.3133 0.01360 0.00739 -0.0821 0.2590 1.0001
6.750 1.3353 0.01399 0.00773 -0.0815 0.2426 1.0001
7.000 1.3558 0.01446 0.00813 -0.0806 0.2230 1.0001
7.250 1.3742 0.01506 0.00862 -0.0795 0.2021 1.0001
7.500 1.3915 0.01570 0.00916 -0.0782 0.1823 1.0001
7.750 1.4077 0.01638 0.00976 -0.0767 0.1667 1.0001
8.000 1.4226 0.01702 0.01035 -0.0750 0.1550 1.0001
8.250 1.4360 0.01769 0.01100 -0.0730 0.1457 1.0001
8.500 1.4514 0.01829 0.01160 -0.0714 0.1380 1.0001
8.750 1.4654 0.01898 0.01229 -0.0697 0.1313 1.0001
9.000 1.4808 0.01961 0.01294 -0.0683 0.1253 1.0001
9.250 1.4934 0.02041 0.01374 -0.0667 0.1189 1.0001
9.500 1.5087 0.02108 0.01445 -0.0654 0.1125 1.0001
9.750 1.5204 0.02199 0.01535 -0.0638 0.1060 1.0001
10.000 1.5346 0.02277 0.01616 -0.0626 0.0994 1.0001
10.250 1.5458 0.02376 0.01717 -0.0611 0.0920 1.0001
10.500 1.5551 0.02494 0.01832 -0.0596 0.0809 1.0001
10.750 1.5561 0.02677 0.02001 -0.0574 0.0584 1.0001
11.000 1.5445 0.02971 0.02275 -0.0545 0.0357 1.0001
11.250 1.5409 0.03221 0.02525 -0.0526 0.0295 1.0001
11.500 1.5417 0.03443 0.02755 -0.0513 0.0266 1.0001
11.750 1.5411 0.03688 0.03006 -0.0501 0.0247 1.0001
12.000 1.5399 0.03951 0.03278 -0.0492 0.0234 1.0001
12.250 1.5411 0.04196 0.03533 -0.0485 0.0225 1.0001
12.500 1.5399 0.04476 0.03825 -0.0479 0.0217 1.0001
12.750 1.5361 0.04794 0.04152 -0.0476 0.0210 1.0001
13.000 1.5285 0.05170 0.04537 -0.0473 0.0204 1.0001
13.500 1.5135 0.05966 0.05357 -0.0477 0.0195 1.0001
13.750 1.5079 0.06357 0.05761 -0.0481 0.0192 1.0001
14.000 1.5007 0.06783 0.06198 -0.0488 0.0188 1.0001
14.250 1.4925 0.07232 0.06660 -0.0496 0.0185 1.0001
14.500 1.4830 0.07709 0.07147 -0.0506 0.0182 1.0001
14.750 1.4729 0.08203 0.07652 -0.0518 0.0179 1.0001
15.000 1.4621 0.08717 0.08178 -0.0531 0.0176 1.0001
15.250 1.4502 0.09255 0.08726 -0.0545 0.0174 1.0001
15.500 1.4377 0.09805 0.09287 -0.0561 0.0172 1.0001
15.750 1.4243 0.10375 0.09866 -0.0578 0.0169 1.0001
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Polar data table (+)
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