NACA CYH (nacacyh-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA CYH (nacacyh-il) Reynolds number: 100,000 Max Cl/Cd: 49.38 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-nacacyh-il-100000-n5.txt Download as CSV file: xf-nacacyh-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA CYH
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4811 0.09058 0.08558 -0.0257 1.0000 0.0480
-10.250 -0.4861 0.08515 0.08020 -0.0293 1.0000 0.0475
-10.000 -0.4950 0.07894 0.07404 -0.0343 1.0000 0.0471
-9.750 -0.5110 0.07202 0.06714 -0.0399 1.0000 0.0466
-9.500 -0.5279 0.06474 0.05978 -0.0438 1.0000 0.0462
-9.250 -0.5429 0.05802 0.05286 -0.0456 1.0000 0.0462
-9.000 -0.5531 0.05269 0.04728 -0.0453 1.0000 0.0467
-8.750 -0.5605 0.04833 0.04263 -0.0436 1.0000 0.0474
-8.500 -0.5667 0.04477 0.03877 -0.0407 1.0000 0.0479
-8.250 -0.5573 0.04064 0.03415 -0.0406 0.9928 0.0483
-8.000 -0.5326 0.03650 0.02938 -0.0424 0.9807 0.0489
-7.750 -0.5051 0.03329 0.02553 -0.0438 0.9695 0.0498
-7.500 -0.4747 0.03108 0.02303 -0.0453 0.9593 0.0513
-7.250 -0.4448 0.02955 0.02130 -0.0463 0.9476 0.0526
-7.000 -0.4151 0.02790 0.01937 -0.0470 0.9360 0.0535
-6.750 -0.3845 0.02639 0.01759 -0.0477 0.9255 0.0545
-6.500 -0.3542 0.02504 0.01600 -0.0481 0.9150 0.0556
-6.250 -0.3256 0.02388 0.01461 -0.0482 0.9035 0.0569
-6.000 -0.2964 0.02292 0.01343 -0.0482 0.8933 0.0589
-5.750 -0.2680 0.02204 0.01239 -0.0481 0.8834 0.0610
-5.500 -0.2416 0.02124 0.01157 -0.0478 0.8727 0.0630
-5.250 -0.2146 0.02053 0.01080 -0.0474 0.8637 0.0651
-5.000 -0.1885 0.01989 0.01008 -0.0468 0.8539 0.0676
-4.750 -0.1627 0.01932 0.00941 -0.0461 0.8447 0.0706
-4.500 -0.1371 0.01872 0.00876 -0.0455 0.8364 0.0744
-4.250 -0.1117 0.01826 0.00828 -0.0449 0.8273 0.0809
-4.000 -0.0858 0.01777 0.00779 -0.0442 0.8197 0.0916
-3.750 -0.0607 0.01730 0.00737 -0.0436 0.8108 0.1087
-3.500 -0.0350 0.01684 0.00699 -0.0430 0.8036 0.1362
-3.250 -0.0099 0.01644 0.00678 -0.0425 0.7944 0.1799
-3.000 0.0153 0.01601 0.00659 -0.0418 0.7863 0.2522
-2.750 0.0386 0.01544 0.00647 -0.0409 0.7755 0.3565
-2.500 0.0589 0.01453 0.00629 -0.0393 0.7649 0.5282
-2.250 0.1082 0.01395 0.00667 -0.0409 0.7541 0.8771
-2.000 0.1464 0.01413 0.00669 -0.0419 0.7423 0.9307
-1.750 0.2106 0.01432 0.00667 -0.0484 0.7326 0.9750
-1.500 0.2768 0.01424 0.00636 -0.0561 0.7237 1.0000
-1.250 0.3016 0.01426 0.00627 -0.0557 0.7136 1.0000
-1.000 0.3262 0.01428 0.00615 -0.0550 0.7047 1.0000
-0.750 0.3507 0.01431 0.00609 -0.0544 0.6947 1.0000
-0.500 0.3751 0.01435 0.00604 -0.0538 0.6850 1.0000
-0.250 0.3995 0.01439 0.00596 -0.0531 0.6758 1.0000
0.000 0.4238 0.01444 0.00597 -0.0526 0.6647 1.0000
0.250 0.4479 0.01450 0.00594 -0.0519 0.6541 1.0000
0.500 0.4720 0.01454 0.00590 -0.0511 0.6439 1.0000
0.750 0.4960 0.01461 0.00594 -0.0505 0.6318 1.0000
1.000 0.5199 0.01469 0.00598 -0.0498 0.6201 1.0000
1.250 0.5437 0.01476 0.00600 -0.0490 0.6080 1.0000
1.500 0.5673 0.01484 0.00601 -0.0482 0.5953 1.0000
1.750 0.5908 0.01493 0.00606 -0.0474 0.5819 1.0000
2.000 0.6142 0.01504 0.00613 -0.0466 0.5678 1.0000
2.250 0.6375 0.01517 0.00622 -0.0458 0.5535 1.0000
2.500 0.6606 0.01532 0.00633 -0.0449 0.5387 1.0000
2.750 0.6835 0.01549 0.00645 -0.0440 0.5234 1.0000
3.000 0.7063 0.01568 0.00660 -0.0432 0.5082 1.0000
3.250 0.7290 0.01590 0.00678 -0.0423 0.4936 1.0000
3.500 0.7516 0.01614 0.00698 -0.0414 0.4792 1.0000
3.750 0.7740 0.01641 0.00721 -0.0406 0.4652 1.0000
4.000 0.7963 0.01669 0.00745 -0.0397 0.4518 1.0000
4.250 0.8183 0.01699 0.00772 -0.0388 0.4382 1.0000
4.500 0.8400 0.01731 0.00799 -0.0378 0.4249 1.0000
4.750 0.8617 0.01765 0.00829 -0.0369 0.4123 1.0000
5.000 0.8834 0.01800 0.00866 -0.0360 0.4004 1.0000
5.250 0.9047 0.01837 0.00902 -0.0351 0.3880 1.0000
5.500 0.9255 0.01875 0.00938 -0.0341 0.3747 1.0000
5.750 0.9461 0.01916 0.00976 -0.0331 0.3618 1.0000
6.000 0.9667 0.01959 0.01016 -0.0322 0.3498 1.0000
6.250 0.9876 0.02000 0.01065 -0.0313 0.3386 1.0000
6.500 1.0084 0.02045 0.01114 -0.0305 0.3282 1.0000
6.750 1.0287 0.02093 0.01162 -0.0295 0.3179 1.0000
7.000 1.0490 0.02138 0.01220 -0.0286 0.3066 1.0000
7.250 1.0688 0.02186 0.01276 -0.0277 0.2955 1.0000
7.500 1.0878 0.02237 0.01333 -0.0267 0.2836 1.0000
7.750 1.1059 0.02289 0.01393 -0.0256 0.2706 1.0000
8.000 1.1234 0.02343 0.01457 -0.0244 0.2564 1.0000
8.250 1.1400 0.02401 0.01524 -0.0232 0.2414 1.0000
8.500 1.1556 0.02465 0.01596 -0.0219 0.2249 1.0000
8.750 1.1689 0.02540 0.01673 -0.0203 0.2061 1.0000
9.000 1.1791 0.02631 0.01761 -0.0185 0.1879 1.0000
9.250 1.1870 0.02737 0.01860 -0.0165 0.1723 1.0000
9.500 1.1927 0.02849 0.01970 -0.0142 0.1590 1.0000
9.750 1.1988 0.02971 0.02093 -0.0122 0.1478 1.0000
10.000 1.2043 0.03105 0.02229 -0.0105 0.1386 1.0000
10.250 1.2098 0.03249 0.02378 -0.0090 0.1301 1.0000
10.500 1.2164 0.03396 0.02534 -0.0078 0.1231 1.0000
10.750 1.2205 0.03568 0.02714 -0.0068 0.1161 1.0000
11.000 1.2256 0.03743 0.02900 -0.0060 0.1088 1.0000
11.250 1.2267 0.03959 0.03121 -0.0054 0.1019 1.0000
11.500 1.2305 0.04165 0.03341 -0.0049 0.0944 1.0000
11.750 1.2288 0.04430 0.03609 -0.0047 0.0874 1.0000
12.000 1.2292 0.04688 0.03881 -0.0046 0.0797 1.0000
12.250 1.2269 0.04984 0.04187 -0.0047 0.0735 1.0000
12.500 1.2231 0.05309 0.04524 -0.0050 0.0663 1.0000
12.750 1.2185 0.05657 0.04884 -0.0055 0.0589 1.0000
13.000 1.2098 0.06068 0.05306 -0.0063 0.0525 1.0000
13.250 1.2001 0.06509 0.05755 -0.0073 0.0466 1.0000
13.500 1.1889 0.06986 0.06241 -0.0086 0.0424 1.0000
13.750 1.1769 0.07500 0.06764 -0.0101 0.0391 1.0000
14.000 1.1639 0.08049 0.07320 -0.0120 0.0369 1.0000
14.250 1.1525 0.08587 0.07870 -0.0138 0.0348 1.0000
14.500 1.1407 0.09147 0.08440 -0.0158 0.0333 1.0000
14.750 1.1286 0.09723 0.09025 -0.0180 0.0320 1.0000
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