USA 22 AIRFOIL (usa22-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: USA 22 AIRFOIL (usa22-il) Reynolds number: 50,000 Max Cl/Cd: 32.51 at α=10.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-usa22-il-50000.txt Download as CSV file: xf-usa22-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: USA 22 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3735 0.10521 0.09902 -0.0134 1.0000 0.1922
-7.500 -0.3467 0.09862 0.09238 -0.0109 1.0000 0.2014
-7.250 -0.3642 0.09901 0.09296 -0.0154 1.0000 0.2066
-7.000 -0.3415 0.09304 0.08698 -0.0116 1.0000 0.2159
-6.500 -0.3378 0.08793 0.08207 -0.0141 1.0000 0.2336
-5.750 -0.3299 0.07998 0.07441 -0.0167 1.0000 0.2657
-5.500 -0.3260 0.07749 0.07198 -0.0165 1.0000 0.2792
-5.250 -0.3168 0.07344 0.06803 -0.0128 1.0000 0.2886
-5.000 -0.3146 0.07075 0.06543 -0.0124 1.0000 0.2997
-4.750 -0.3129 0.06824 0.06298 -0.0121 1.0000 0.3124
-4.500 -0.3110 0.06575 0.06057 -0.0113 1.0000 0.3263
-4.250 -0.3088 0.06326 0.05815 -0.0098 1.0000 0.3415
-4.000 -0.3076 0.06137 0.05630 -0.0099 1.0000 0.3664
-3.750 -0.3071 0.05858 0.05363 -0.0056 1.0000 0.3856
-3.500 -0.3072 0.05632 0.05145 -0.0029 1.0000 0.4141
-3.250 -0.1738 0.04181 0.03473 -0.0462 1.0000 0.1630
-3.000 -0.1513 0.03889 0.03157 -0.0474 1.0000 0.1617
-2.750 -0.1237 0.03598 0.02815 -0.0494 1.0000 0.1623
-2.500 -0.0945 0.03335 0.02499 -0.0513 1.0000 0.1624
-2.250 -0.0736 0.03238 0.02397 -0.0519 1.0000 0.1717
-2.000 -0.0180 0.03009 0.02105 -0.0579 0.9898 0.1821
-1.750 0.0470 0.02869 0.01924 -0.0653 0.9727 0.2081
-1.500 0.1072 0.02770 0.01811 -0.0714 0.9543 0.2430
-1.250 0.1629 0.02654 0.01689 -0.0761 0.9351 0.3252
-1.000 0.2169 0.02409 0.01504 -0.0806 0.9196 0.4914
-0.750 0.2724 0.02212 0.01434 -0.0843 0.9021 1.0000
-0.500 0.3288 0.02231 0.01389 -0.0891 0.8835 1.0000
-0.250 0.3661 0.02265 0.01385 -0.0906 0.8615 1.0000
0.000 0.4058 0.02286 0.01373 -0.0922 0.8429 1.0000
0.250 0.4427 0.02304 0.01363 -0.0930 0.8257 1.0000
0.500 0.4708 0.02346 0.01384 -0.0927 0.8070 1.0000
0.750 0.4993 0.02384 0.01403 -0.0924 0.7897 1.0000
1.000 0.5275 0.02422 0.01424 -0.0919 0.7736 1.0000
1.250 0.5548 0.02462 0.01451 -0.0912 0.7582 1.0000
1.500 0.5812 0.02507 0.01483 -0.0905 0.7431 1.0000
1.750 0.6069 0.02556 0.01521 -0.0896 0.7283 1.0000
2.000 0.6320 0.02609 0.01564 -0.0887 0.7137 1.0000
2.250 0.6567 0.02666 0.01613 -0.0878 0.6992 1.0000
2.500 0.6810 0.02726 0.01668 -0.0868 0.6847 1.0000
2.750 0.7050 0.02787 0.01724 -0.0858 0.6703 1.0000
3.000 0.7288 0.02852 0.01785 -0.0848 0.6560 1.0000
3.250 0.7524 0.02917 0.01847 -0.0837 0.6417 1.0000
3.500 0.7759 0.02986 0.01918 -0.0827 0.6275 1.0000
3.750 0.7992 0.03056 0.01988 -0.0816 0.6134 1.0000
4.000 0.8224 0.03129 0.02061 -0.0805 0.5992 1.0000
4.250 0.8454 0.03206 0.02140 -0.0795 0.5852 1.0000
4.500 0.8684 0.03286 0.02227 -0.0784 0.5713 1.0000
4.750 0.8912 0.03368 0.02313 -0.0773 0.5575 1.0000
5.000 0.9143 0.03452 0.02401 -0.0763 0.5442 1.0000
5.250 0.9384 0.03527 0.02480 -0.0752 0.5314 1.0000
5.500 0.9619 0.03611 0.02574 -0.0742 0.5188 1.0000
5.750 0.9804 0.03764 0.02741 -0.0733 0.5054 1.0000
6.000 0.9976 0.03932 0.02925 -0.0725 0.4924 1.0000
6.250 1.0135 0.04124 0.03133 -0.0718 0.4800 1.0000
6.500 1.0292 0.04333 0.03362 -0.0711 0.4693 1.0000
6.750 1.0570 0.04395 0.03431 -0.0701 0.4606 1.0000
7.000 1.0579 0.04784 0.03847 -0.0698 0.4493 1.0000
7.250 1.0587 0.05180 0.04262 -0.0695 0.4396 1.0000
7.500 1.0836 0.05289 0.04385 -0.0685 0.4323 1.0000
7.750 1.0250 0.06457 0.05565 -0.0713 0.4251 1.0000
8.000 0.9698 0.07575 0.06672 -0.0753 0.4220 1.0000
8.250 0.9999 0.07640 0.06756 -0.0737 0.4154 1.0000
8.500 0.9628 0.08539 0.07648 -0.0770 0.4151 1.0000
8.750 0.9570 0.09109 0.08223 -0.0786 0.4162 1.0000
9.250 1.2343 0.05310 0.04535 -0.0555 0.3395 1.0000
9.500 1.2037 0.06056 0.05305 -0.0552 0.3358 1.0000
9.750 1.1743 0.06787 0.06046 -0.0555 0.3323 1.0000
10.000 1.1451 0.07580 0.06840 -0.0568 0.3300 1.0000
10.250 1.3114 0.04034 0.03274 -0.0408 0.2070 1.0000
10.500 1.2976 0.04268 0.03500 -0.0378 0.1734 1.0000
10.750 1.2823 0.04617 0.03839 -0.0362 0.1419 1.0000
11.000 1.2669 0.05037 0.04243 -0.0358 0.1213 1.0000
11.250 1.2526 0.05500 0.04692 -0.0362 0.1094 1.0000
11.500 1.2399 0.05976 0.05164 -0.0368 0.1016 1.0000
11.750 1.2287 0.06443 0.05624 -0.0375 0.0963 1.0000
12.000 1.2204 0.06882 0.06064 -0.0378 0.0914 1.0000
12.250 1.2131 0.07297 0.06470 -0.0380 0.0877 1.0000
12.500 1.2114 0.07647 0.06828 -0.0375 0.0841 1.0000
12.750 1.2122 0.07970 0.07162 -0.0368 0.0807 1.0000
13.000 1.2160 0.08243 0.07434 -0.0356 0.0775 1.0000
13.250 1.2253 0.08453 0.07642 -0.0334 0.0743 1.0000
13.500 1.2246 0.08862 0.08081 -0.0335 0.0725 1.0000
13.750 1.2209 0.09325 0.08571 -0.0342 0.0711 1.0000
14.000 1.2135 0.09856 0.09127 -0.0355 0.0703 1.0000
14.250 1.2006 0.10499 0.09797 -0.0380 0.0702 1.0000
14.500 1.1810 0.11296 0.10619 -0.0419 0.0709 1.0000
14.750 1.1567 0.12241 0.11587 -0.0471 0.0723 1.0000
15.000 1.1333 0.13242 0.12602 -0.0526 0.0738 1.0000
15.250 1.1146 0.14199 0.13566 -0.0576 0.0750 1.0000
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