NACA 66(2)-215 (naca662215-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 66(2)-215 (naca662215-il) Reynolds number: 50,000 Max Cl/Cd: 20.95 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca662215-il-50000-n5.txt Download as CSV file: xf-naca662215-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 66(2)-215
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.4795 0.10974 0.10227 -0.0614 1.0000 0.0618
-12.250 -0.4899 0.10369 0.09628 -0.0640 1.0000 0.0608
-12.000 -0.5084 0.09652 0.08916 -0.0676 1.0000 0.0596
-11.750 -0.5391 0.08961 0.08229 -0.0706 1.0000 0.0584
-11.500 -0.5775 0.08424 0.07692 -0.0712 1.0000 0.0575
-11.250 -0.6167 0.08059 0.07325 -0.0691 1.0000 0.0568
-11.000 -0.6579 0.07807 0.07067 -0.0651 1.0000 0.0562
-10.750 -0.6994 0.07624 0.06878 -0.0598 1.0000 0.0558
-10.500 -0.7431 0.07507 0.06750 -0.0530 1.0000 0.0553
-10.000 -0.8072 0.07223 0.06426 -0.0406 0.9992 0.0546
-9.750 -0.8098 0.06865 0.06038 -0.0396 0.9937 0.0546
-9.500 -0.8105 0.06529 0.05669 -0.0383 0.9884 0.0545
-9.250 -0.8081 0.06204 0.05306 -0.0371 0.9836 0.0546
-8.750 -0.7935 0.05602 0.04635 -0.0347 0.9750 0.0550
-8.500 -0.7831 0.05354 0.04365 -0.0334 0.9714 0.0559
-8.250 -0.7696 0.05149 0.04145 -0.0324 0.9680 0.0573
-8.000 -0.7537 0.04947 0.03915 -0.0317 0.9649 0.0590
-7.750 -0.7344 0.04737 0.03669 -0.0313 0.9622 0.0605
-7.500 -0.7184 0.04548 0.03445 -0.0298 0.9586 0.0614
-7.250 -0.6961 0.04364 0.03226 -0.0292 0.9558 0.0626
-7.000 -0.6698 0.04207 0.03032 -0.0291 0.9534 0.0644
-6.750 -0.6393 0.04055 0.02866 -0.0298 0.9518 0.0673
-6.500 -0.6064 0.03936 0.02741 -0.0309 0.9505 0.0707
-6.250 -0.5670 0.03834 0.02624 -0.0325 0.9497 0.0739
-6.000 -0.5349 0.03769 0.02535 -0.0328 0.9481 0.0782
-5.750 -0.5132 0.03687 0.02459 -0.0319 0.9456 0.0832
-5.500 -0.4944 0.03623 0.02385 -0.0306 0.9426 0.0883
-5.250 -0.4767 0.03553 0.02306 -0.0293 0.9396 0.0935
-5.000 -0.4603 0.03480 0.02233 -0.0280 0.9370 0.1024
-4.750 -0.4467 0.03404 0.02161 -0.0263 0.9346 0.1154
-4.500 -0.4453 0.03328 0.02098 -0.0223 0.9312 0.1324
-4.250 -0.4441 0.03208 0.02023 -0.0187 0.9275 0.1827
-4.000 -0.4552 0.02990 0.01946 -0.0133 0.9238 0.3832
-3.750 -0.4331 0.03213 0.02298 -0.0065 0.9221 0.7045
-3.500 -0.3483 0.03862 0.02919 -0.0053 0.9238 0.8271
-3.250 -0.2944 0.03936 0.02957 -0.0091 0.9233 0.8476
-3.000 -0.2553 0.03940 0.02932 -0.0118 0.9220 0.8564
-2.750 -0.2270 0.03935 0.02905 -0.0127 0.9201 0.8651
-2.500 -0.2076 0.03926 0.02880 -0.0119 0.9170 0.8732
-2.250 -0.1911 0.03915 0.02854 -0.0108 0.9138 0.8809
-2.000 -0.1650 0.03908 0.02832 -0.0114 0.9112 0.8873
-1.750 -0.1481 0.03902 0.02813 -0.0104 0.9081 0.8947
-1.500 -0.1127 0.03898 0.02794 -0.0129 0.9060 0.8992
-1.250 -0.0897 0.03897 0.02783 -0.0130 0.9033 0.9050
-1.000 -0.0805 0.03889 0.02768 -0.0106 0.8990 0.9111
-0.750 -0.0545 0.03886 0.02757 -0.0114 0.8955 0.9153
-0.500 -0.0323 0.03887 0.02751 -0.0114 0.8921 0.9201
-0.250 -0.0091 0.03893 0.02750 -0.0116 0.8890 0.9247
0.000 0.0123 0.03894 0.02747 -0.0116 0.8850 0.9283
0.250 0.0308 0.03896 0.02747 -0.0110 0.8803 0.9326
0.500 0.0494 0.03903 0.02751 -0.0103 0.8762 0.9369
0.750 0.0805 0.03917 0.02763 -0.0120 0.8729 0.9397
1.000 0.0963 0.03922 0.02769 -0.0110 0.8673 0.9431
1.250 0.1170 0.03932 0.02780 -0.0108 0.8622 0.9465
1.500 0.1432 0.03949 0.02798 -0.0115 0.8580 0.9498
1.750 0.1611 0.03962 0.02815 -0.0109 0.8521 0.9530
2.000 0.1840 0.03976 0.02834 -0.0111 0.8460 0.9556
2.250 0.2163 0.03997 0.02861 -0.0129 0.8415 0.9581
2.500 0.2294 0.04015 0.02886 -0.0114 0.8342 0.9624
2.750 0.2567 0.04036 0.02915 -0.0123 0.8281 0.9651
3.000 0.2918 0.04061 0.02950 -0.0146 0.8234 0.9671
3.250 0.3054 0.04082 0.02982 -0.0133 0.8141 0.9707
3.750 0.3574 0.04128 0.03053 -0.0146 0.7988 0.9770
4.250 0.4140 0.04167 0.03126 -0.0166 0.7816 0.9834
4.500 0.4452 0.04180 0.03157 -0.0178 0.7731 0.9861
4.750 0.4753 0.04187 0.03186 -0.0189 0.7632 0.9889
5.000 0.4984 0.04199 0.03218 -0.0188 0.7512 0.9927
5.250 0.5295 0.04193 0.03237 -0.0198 0.7400 0.9961
5.500 0.5719 0.04148 0.03223 -0.0220 0.7299 0.9987
5.750 0.5915 0.04105 0.03205 -0.0203 0.7149 1.0000
6.000 0.5951 0.04020 0.03135 -0.0155 0.6921 1.0000
6.250 0.6124 0.03691 0.02820 -0.0097 0.6457 1.0000
6.500 0.6020 0.03577 0.02709 -0.0024 0.6033 1.0000
6.750 0.6027 0.03418 0.02553 0.0039 0.5453 1.0000
7.000 0.6544 0.03123 0.02101 0.0068 0.2867 1.0000
7.250 0.6359 0.03235 0.02159 0.0130 0.2152 1.0000
7.500 0.6211 0.03353 0.02230 0.0185 0.1620 1.0000
7.750 0.6127 0.03467 0.02311 0.0230 0.1310 1.0000
8.000 0.6113 0.03588 0.02406 0.0263 0.1127 1.0000
8.250 0.6163 0.03705 0.02516 0.0286 0.0999 1.0000
8.500 0.6264 0.03817 0.02628 0.0304 0.0912 1.0000
8.750 0.6386 0.03937 0.02742 0.0318 0.0855 1.0000
9.000 0.6579 0.04031 0.02849 0.0328 0.0794 1.0000
9.250 0.6801 0.04134 0.02949 0.0333 0.0737 1.0000
9.500 0.7220 0.04214 0.03045 0.0327 0.0692 1.0000
9.750 0.7622 0.04325 0.03172 0.0317 0.0642 1.0000
10.000 0.8084 0.04498 0.03343 0.0296 0.0603 1.0000
10.250 0.8475 0.04719 0.03605 0.0283 0.0583 1.0000
10.500 0.8733 0.04953 0.03874 0.0282 0.0565 1.0000
10.750 0.8898 0.05177 0.04123 0.0288 0.0544 1.0000
11.000 0.9046 0.05407 0.04371 0.0294 0.0527 1.0000
11.250 0.9177 0.05663 0.04646 0.0301 0.0514 1.0000
11.500 0.9274 0.05956 0.04960 0.0310 0.0508 1.0000
11.750 0.9294 0.06262 0.05291 0.0325 0.0505 1.0000
12.000 0.9229 0.06563 0.05624 0.0347 0.0504 1.0000
12.250 0.9134 0.06882 0.05971 0.0366 0.0503 1.0000
12.500 0.9017 0.07219 0.06335 0.0382 0.0503 1.0000
12.750 0.8871 0.07585 0.06726 0.0395 0.0503 1.0000
13.000 0.8690 0.07989 0.07154 0.0403 0.0503 1.0000
13.250 0.8519 0.08417 0.07603 0.0404 0.0504 1.0000
13.500 0.8325 0.08894 0.08098 0.0398 0.0505 1.0000
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