NACA 5-H-10 AIRFOIL (n5h10-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 5-H-10 AIRFOIL (n5h10-il) Reynolds number: 50,000 Max Cl/Cd: 31.91 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n5h10-il-50000-n5.txt Download as CSV file: xf-n5h10-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 5-H-10 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4877 0.10445 0.09832 -0.0118 1.0000 0.1152
-9.000 -0.4988 0.10131 0.09530 -0.0170 1.0000 0.1200
-8.750 -0.5193 0.09832 0.09244 -0.0230 1.0000 0.1211
-8.500 -0.4914 0.09277 0.08689 -0.0204 1.0000 0.1249
-8.250 -0.4998 0.08376 0.07781 -0.0291 1.0000 0.0624
-8.000 -0.4950 0.07956 0.07360 -0.0298 1.0000 0.0595
-7.750 -0.4954 0.07532 0.06934 -0.0313 1.0000 0.0570
-7.250 -0.5080 0.06672 0.06032 -0.0328 1.0000 0.0503
-7.000 -0.5110 0.06389 0.05746 -0.0306 0.9993 0.0498
-6.750 -0.4957 0.05940 0.05268 -0.0324 0.9777 0.0493
-6.500 -0.4785 0.05487 0.04768 -0.0342 0.9638 0.0497
-6.250 -0.4612 0.05077 0.04301 -0.0351 0.9522 0.0510
-6.000 -0.4388 0.04733 0.03948 -0.0364 0.9436 0.0537
-5.750 -0.4163 0.04376 0.03540 -0.0369 0.9350 0.0541
-5.500 -0.3946 0.04072 0.03186 -0.0367 0.9261 0.0550
-5.250 -0.3698 0.03825 0.02887 -0.0368 0.9189 0.0593
-5.000 -0.3468 0.03594 0.02592 -0.0360 0.9105 0.0623
-4.750 -0.3186 0.03370 0.02297 -0.0357 0.9040 0.0639
-4.500 -0.2939 0.03177 0.02095 -0.0357 0.8965 0.0691
-4.250 -0.2631 0.03023 0.01898 -0.0360 0.8908 0.0752
-4.000 -0.2328 0.02882 0.01712 -0.0360 0.8838 0.0780
-3.750 -0.1965 0.02730 0.01552 -0.0374 0.8788 0.0843
-3.500 -0.1611 0.02637 0.01435 -0.0386 0.8730 0.0941
-3.250 -0.1276 0.02545 0.01331 -0.0395 0.8675 0.1001
-3.000 -0.0991 0.02481 0.01246 -0.0394 0.8619 0.1077
-2.500 0.1121 0.02074 0.01090 -0.0643 0.8661 1.0000
-2.250 0.1353 0.02089 0.01077 -0.0640 0.8589 1.0000
-2.000 0.1584 0.02105 0.01067 -0.0635 0.8524 1.0000
-1.750 0.1812 0.02125 0.01065 -0.0631 0.8456 1.0000
-1.500 0.2039 0.02145 0.01067 -0.0626 0.8395 1.0000
-1.250 0.2266 0.02169 0.01076 -0.0622 0.8333 1.0000
-1.000 0.2491 0.02193 0.01086 -0.0617 0.8274 1.0000
-0.750 0.2717 0.02220 0.01100 -0.0612 0.8220 1.0000
-0.500 0.2935 0.02250 0.01124 -0.0607 0.8157 1.0000
-0.250 0.3158 0.02278 0.01143 -0.0601 0.8108 1.0000
0.000 0.3375 0.02315 0.01176 -0.0597 0.8051 1.0000
0.250 0.3598 0.02350 0.01207 -0.0593 0.7997 1.0000
0.500 0.3822 0.02381 0.01234 -0.0586 0.7954 1.0000
0.750 0.4021 0.02430 0.01285 -0.0581 0.7892 1.0000
1.000 0.4233 0.02470 0.01326 -0.0574 0.7843 1.0000
1.250 0.4443 0.02511 0.01369 -0.0566 0.7796 1.0000
1.500 0.4627 0.02567 0.01432 -0.0558 0.7735 1.0000
1.750 0.4834 0.02611 0.01480 -0.0549 0.7689 1.0000
2.000 0.5018 0.02667 0.01542 -0.0539 0.7634 1.0000
2.250 0.5195 0.02720 0.01604 -0.0528 0.7569 1.0000
2.500 0.5403 0.02755 0.01648 -0.0515 0.7513 1.0000
2.750 0.5556 0.02807 0.01709 -0.0498 0.7420 1.0000
3.000 0.5730 0.02838 0.01751 -0.0480 0.7327 1.0000
3.250 0.5941 0.02849 0.01775 -0.0463 0.7245 1.0000
3.500 0.6080 0.02904 0.01843 -0.0444 0.7146 1.0000
3.750 0.6303 0.02923 0.01877 -0.0431 0.7093 1.0000
4.000 0.6416 0.02998 0.01968 -0.0411 0.6996 1.0000
4.250 0.6604 0.03033 0.02025 -0.0396 0.6928 1.0000
4.500 0.6768 0.03066 0.02077 -0.0375 0.6831 1.0000
4.750 0.6926 0.03081 0.02111 -0.0351 0.6709 1.0000
5.000 0.7123 0.03043 0.02094 -0.0325 0.6564 1.0000
5.250 0.7359 0.02948 0.02023 -0.0295 0.6395 1.0000
5.500 0.7542 0.02848 0.01944 -0.0258 0.6157 1.0000
5.750 0.7734 0.02721 0.01836 -0.0218 0.5867 1.0000
6.000 0.7891 0.02620 0.01752 -0.0177 0.5499 1.0000
6.250 0.7928 0.02612 0.01757 -0.0134 0.4903 1.0000
6.500 0.8056 0.02525 0.01571 -0.0077 0.3331 1.0000
6.750 0.8002 0.02687 0.01676 -0.0032 0.2301 1.0000
7.000 0.7893 0.02893 0.01817 0.0012 0.1704 1.0000
7.250 0.7825 0.03080 0.01974 0.0051 0.1414 1.0000
7.500 0.7783 0.03256 0.02134 0.0088 0.1221 1.0000
7.750 0.7774 0.03417 0.02288 0.0121 0.1084 1.0000
8.000 0.7815 0.03568 0.02438 0.0147 0.0966 1.0000
8.250 0.7892 0.03711 0.02583 0.0170 0.0853 1.0000
8.500 0.8016 0.03852 0.02721 0.0190 0.0780 1.0000
8.750 0.8217 0.03976 0.02863 0.0206 0.0691 1.0000
9.000 0.8535 0.04115 0.03028 0.0215 0.0606 1.0000
9.250 0.8847 0.04293 0.03209 0.0218 0.0543 1.0000
9.500 0.9179 0.04551 0.03512 0.0218 0.0489 1.0000
9.750 0.9391 0.04821 0.03811 0.0226 0.0459 1.0000
10.000 0.9537 0.05092 0.04087 0.0234 0.0431 1.0000
10.250 0.9576 0.05399 0.04439 0.0254 0.0414 1.0000
10.500 0.9564 0.05716 0.04797 0.0276 0.0404 1.0000
10.750 0.9511 0.06040 0.05154 0.0297 0.0400 1.0000
11.000 0.9415 0.06383 0.05526 0.0313 0.0397 1.0000
11.250 0.9287 0.06751 0.05921 0.0325 0.0395 1.0000
11.500 0.9134 0.07150 0.06343 0.0330 0.0395 1.0000
11.750 0.8963 0.07585 0.06800 0.0328 0.0395 1.0000
12.000 0.8779 0.08066 0.07299 0.0317 0.0397 1.0000
12.250 0.8577 0.08609 0.07857 0.0298 0.0399 1.0000
12.500 0.8388 0.09190 0.08450 0.0272 0.0404 1.0000
12.750 0.8177 0.09876 0.09144 0.0236 0.0407 1.0000
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Polar data table (+)
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