NACA CYH (nacacyh-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA CYH (nacacyh-il) Reynolds number: 50,000 Max Cl/Cd: 33.25 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-nacacyh-il-50000-n5.txt Download as CSV file: xf-nacacyh-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4508 0.09759 0.09052 -0.0244 1.0000 0.0795
-10.000 -0.4547 0.09258 0.08557 -0.0277 1.0000 0.0776
-9.500 -0.5030 0.07654 0.06954 -0.0421 1.0000 0.0720
-9.250 -0.5056 0.07226 0.06522 -0.0429 1.0000 0.0717
-9.000 -0.5116 0.06775 0.06060 -0.0436 1.0000 0.0716
-8.750 -0.5193 0.06326 0.05592 -0.0436 1.0000 0.0719
-8.250 -0.5169 0.05709 0.04961 -0.0410 1.0000 0.0736
-8.000 -0.5156 0.05446 0.04687 -0.0391 1.0000 0.0743
-7.750 -0.5170 0.05159 0.04380 -0.0367 1.0000 0.0745
-7.500 -0.5185 0.04888 0.04084 -0.0340 1.0000 0.0745
-7.250 -0.5177 0.04649 0.03816 -0.0313 1.0000 0.0747
-7.000 -0.5143 0.04429 0.03569 -0.0288 1.0000 0.0750
-6.750 -0.4895 0.04142 0.03240 -0.0300 0.9928 0.0759
-6.500 -0.4572 0.03897 0.02957 -0.0322 0.9838 0.0782
-6.250 -0.4253 0.03671 0.02685 -0.0340 0.9744 0.0814
-6.000 -0.3925 0.03452 0.02410 -0.0355 0.9654 0.0838
-5.750 -0.3564 0.03256 0.02162 -0.0373 0.9578 0.0855
-5.500 -0.3226 0.03094 0.01985 -0.0388 0.9492 0.0878
-5.250 -0.2862 0.02964 0.01841 -0.0406 0.9417 0.0912
-5.000 -0.2503 0.02858 0.01713 -0.0421 0.9336 0.0974
-4.750 -0.2133 0.02752 0.01600 -0.0439 0.9264 0.1043
-4.500 -0.1780 0.02663 0.01496 -0.0451 0.9180 0.1124
-4.250 -0.1404 0.02572 0.01402 -0.0468 0.9110 0.1239
-4.000 -0.1073 0.02498 0.01329 -0.0479 0.9021 0.1457
-3.750 -0.0752 0.02420 0.01273 -0.0488 0.8939 0.1822
-3.500 -0.0464 0.02345 0.01237 -0.0493 0.8850 0.2538
-3.250 -0.0224 0.02255 0.01207 -0.0488 0.8758 0.3629
-3.000 -0.0004 0.02129 0.01178 -0.0473 0.8679 0.5443
-2.750 0.1600 0.02067 0.01162 -0.0687 0.8740 1.0000
-2.500 0.1874 0.02070 0.01137 -0.0687 0.8631 1.0000
-2.250 0.2138 0.02073 0.01116 -0.0684 0.8514 1.0000
-2.000 0.2375 0.02079 0.01099 -0.0675 0.8374 1.0000
-1.750 0.2608 0.02082 0.01083 -0.0664 0.8228 1.0000
-1.500 0.2835 0.02086 0.01068 -0.0651 0.8082 1.0000
-1.250 0.3059 0.02093 0.01058 -0.0638 0.7942 1.0000
-1.000 0.3284 0.02102 0.01051 -0.0626 0.7815 1.0000
-0.750 0.3520 0.02109 0.01043 -0.0614 0.7704 1.0000
-0.500 0.3733 0.02127 0.01051 -0.0602 0.7578 1.0000
-0.250 0.3950 0.02146 0.01061 -0.0590 0.7455 1.0000
0.000 0.4177 0.02162 0.01067 -0.0579 0.7339 1.0000
0.250 0.4415 0.02170 0.01064 -0.0568 0.7232 1.0000
0.500 0.4626 0.02193 0.01082 -0.0555 0.7099 1.0000
0.750 0.4841 0.02215 0.01099 -0.0543 0.6971 1.0000
1.000 0.5061 0.02233 0.01112 -0.0531 0.6847 1.0000
1.250 0.5289 0.02247 0.01120 -0.0519 0.6726 1.0000
1.500 0.5514 0.02261 0.01130 -0.0507 0.6601 1.0000
1.750 0.5725 0.02285 0.01152 -0.0495 0.6462 1.0000
2.000 0.5937 0.02307 0.01174 -0.0482 0.6324 1.0000
2.250 0.6152 0.02329 0.01194 -0.0470 0.6186 1.0000
2.500 0.6369 0.02350 0.01214 -0.0458 0.6050 1.0000
2.750 0.6589 0.02371 0.01235 -0.0446 0.5916 1.0000
3.000 0.6813 0.02390 0.01252 -0.0434 0.5786 1.0000
3.250 0.7045 0.02407 0.01266 -0.0423 0.5661 1.0000
3.500 0.7256 0.02440 0.01303 -0.0412 0.5522 1.0000
3.750 0.7469 0.02476 0.01341 -0.0401 0.5388 1.0000
4.000 0.7685 0.02513 0.01380 -0.0391 0.5260 1.0000
4.250 0.7908 0.02549 0.01419 -0.0381 0.5140 1.0000
4.500 0.8145 0.02577 0.01444 -0.0373 0.5032 1.0000
4.750 0.8353 0.02625 0.01498 -0.0362 0.4906 1.0000
5.000 0.8560 0.02675 0.01554 -0.0352 0.4782 1.0000
5.250 0.8773 0.02719 0.01604 -0.0342 0.4660 1.0000
5.500 0.8993 0.02757 0.01644 -0.0333 0.4542 1.0000
5.750 0.9216 0.02793 0.01681 -0.0323 0.4424 1.0000
6.000 0.9407 0.02852 0.01752 -0.0312 0.4295 1.0000
6.250 0.9602 0.02908 0.01816 -0.0301 0.4168 1.0000
6.500 0.9797 0.02959 0.01873 -0.0290 0.4037 1.0000
6.750 0.9988 0.03008 0.01926 -0.0277 0.3898 1.0000
7.000 1.0172 0.03059 0.01984 -0.0265 0.3754 1.0000
7.250 1.0351 0.03115 0.02044 -0.0252 0.3612 1.0000
7.500 1.0530 0.03175 0.02108 -0.0239 0.3473 1.0000
7.750 1.0708 0.03238 0.02174 -0.0227 0.3337 1.0000
8.000 1.0849 0.03324 0.02274 -0.0212 0.3196 1.0000
8.250 1.0981 0.03415 0.02382 -0.0196 0.3055 1.0000
8.500 1.1100 0.03512 0.02491 -0.0180 0.2914 1.0000
8.750 1.1208 0.03615 0.02607 -0.0163 0.2774 1.0000
9.000 1.1306 0.03725 0.02730 -0.0145 0.2640 1.0000
9.250 1.1393 0.03840 0.02855 -0.0127 0.2512 1.0000
9.500 1.1465 0.03955 0.02978 -0.0108 0.2393 1.0000
9.750 1.1514 0.04084 0.03116 -0.0088 0.2280 1.0000
10.000 1.1541 0.04251 0.03297 -0.0069 0.2173 1.0000
10.250 1.1599 0.04410 0.03464 -0.0055 0.2081 1.0000
10.500 1.1677 0.04558 0.03617 -0.0043 0.1998 1.0000
10.750 1.1698 0.04774 0.03850 -0.0031 0.1916 1.0000
11.000 1.1775 0.04919 0.03992 -0.0021 0.1838 1.0000
11.250 1.1739 0.05193 0.04288 -0.0013 0.1761 1.0000
11.500 1.1762 0.05392 0.04489 -0.0006 0.1683 1.0000
11.750 1.1705 0.05698 0.04812 -0.0003 0.1608 1.0000
12.000 1.1678 0.05963 0.05081 0.0000 0.1533 1.0000
12.250 1.1595 0.06317 0.05449 -0.0003 0.1461 1.0000
12.500 1.1532 0.06650 0.05788 -0.0006 0.1390 1.0000
12.750 1.1419 0.07078 0.06233 -0.0015 0.1324 1.0000
13.000 1.1346 0.07449 0.06608 -0.0023 0.1256 1.0000
13.250 1.1191 0.07987 0.07168 -0.0040 0.1199 1.0000
13.500 1.1129 0.08357 0.07535 -0.0051 0.1129 1.0000
13.750 1.0938 0.09018 0.08222 -0.0075 0.1082 1.0000
14.000 1.0941 0.09294 0.08489 -0.0083 0.1010 1.0000
14.250 1.0713 0.10091 0.09316 -0.0115 0.0976 1.0000
14.500 1.0520 0.10841 0.10085 -0.0147 0.0935 1.0000
14.750 1.0504 0.11199 0.10440 -0.0160 0.0867 1.0000
15.000 1.0181 0.12312 0.11576 -0.0210 0.0847 1.0000
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Polar data table (+)
Polar graphs
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