NACA CYH (nacacyh-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA CYH (nacacyh-il) Reynolds number: 50,000 Max Cl/Cd: 25.75 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-nacacyh-il-50000.txt Download as CSV file: xf-nacacyh-il-50000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4213 0.11394 0.10700 -0.0049 1.0000 0.2587
-10.000 -0.4080 0.10974 0.10282 -0.0046 1.0000 0.2678
-9.750 -0.4370 0.10960 0.10285 -0.0074 1.0000 0.2770
-9.500 -0.4055 0.10408 0.09728 -0.0056 1.0000 0.2906
-9.250 -0.3954 0.10024 0.09347 -0.0055 1.0000 0.2998
-8.750 -0.4123 0.09599 0.08944 -0.0066 1.0000 0.3257
-8.500 -0.3886 0.09154 0.08497 -0.0054 1.0000 0.3395
-8.250 -0.3831 0.08850 0.08199 -0.0048 1.0000 0.3556
-8.000 -0.3890 0.08625 0.07985 -0.0039 1.0000 0.3739
-7.750 -0.3912 0.08360 0.07733 -0.0025 1.0000 0.3926
-7.500 -0.3623 0.07960 0.07330 -0.0010 1.0000 0.4145
-7.250 -0.3639 0.07742 0.07124 0.0011 1.0000 0.4378
-6.750 -0.3717 0.07351 0.06757 0.0079 1.0000 0.4893
-5.750 -0.4764 0.04956 0.04213 -0.0175 1.0000 0.1775
-5.500 -0.4641 0.04531 0.03707 -0.0174 1.0000 0.1645
-5.250 -0.4489 0.04266 0.03423 -0.0165 1.0000 0.1619
-5.000 -0.4319 0.04015 0.03135 -0.0158 1.0000 0.1598
-4.750 -0.4131 0.03804 0.02882 -0.0151 1.0000 0.1607
-4.500 -0.3921 0.03620 0.02652 -0.0147 1.0000 0.1626
-4.250 -0.3696 0.03453 0.02440 -0.0142 1.0000 0.1642
-4.000 -0.3467 0.03298 0.02254 -0.0138 1.0000 0.1665
-3.750 -0.3247 0.03181 0.02129 -0.0134 1.0000 0.1711
-3.500 -0.3020 0.03095 0.02014 -0.0129 1.0000 0.1797
-3.250 -0.2800 0.03009 0.01932 -0.0125 1.0000 0.1905
-3.000 -0.2562 0.02930 0.01846 -0.0122 1.0000 0.2042
-2.750 -0.2317 0.02868 0.01781 -0.0119 1.0000 0.2296
-2.500 -0.2064 0.02794 0.01733 -0.0118 1.0000 0.2789
-2.250 -0.1229 0.02454 0.01675 -0.0191 0.9950 1.0000
-2.000 -0.0679 0.02543 0.01700 -0.0252 0.9820 1.0000
-1.750 -0.0159 0.02621 0.01734 -0.0308 0.9664 1.0000
-1.500 0.0345 0.02693 0.01773 -0.0358 0.9501 1.0000
-1.250 0.0821 0.02759 0.01811 -0.0403 0.9340 1.0000
-1.000 0.1271 0.02821 0.01852 -0.0441 0.9184 1.0000
-0.750 0.1704 0.02880 0.01892 -0.0476 0.9031 1.0000
-0.500 0.2128 0.02935 0.01934 -0.0507 0.8878 1.0000
-0.250 0.2554 0.02987 0.01974 -0.0537 0.8723 1.0000
0.000 0.2984 0.03034 0.02011 -0.0567 0.8565 1.0000
0.250 0.3406 0.03076 0.02048 -0.0593 0.8405 1.0000
0.500 0.3767 0.03118 0.02084 -0.0607 0.8239 1.0000
0.750 0.4097 0.03161 0.02123 -0.0614 0.8070 1.0000
1.000 0.4402 0.03205 0.02165 -0.0616 0.7900 1.0000
1.250 0.4687 0.03251 0.02208 -0.0614 0.7729 1.0000
1.500 0.4957 0.03298 0.02253 -0.0609 0.7560 1.0000
1.750 0.5210 0.03349 0.02304 -0.0601 0.7393 1.0000
2.000 0.5449 0.03405 0.02358 -0.0591 0.7230 1.0000
2.250 0.5674 0.03467 0.02420 -0.0579 0.7073 1.0000
2.500 0.5891 0.03535 0.02490 -0.0568 0.6924 1.0000
2.750 0.6131 0.03591 0.02546 -0.0557 0.6787 1.0000
3.000 0.6430 0.03610 0.02566 -0.0551 0.6668 1.0000
3.250 0.6556 0.03735 0.02693 -0.0534 0.6523 1.0000
3.500 0.6668 0.03876 0.02837 -0.0517 0.6385 1.0000
3.750 0.6784 0.04021 0.02985 -0.0502 0.6254 1.0000
4.000 0.6978 0.04119 0.03088 -0.0491 0.6144 1.0000
4.250 0.7277 0.04133 0.03108 -0.0484 0.6043 1.0000
4.500 0.7312 0.04348 0.03328 -0.0467 0.5911 1.0000
4.750 0.7379 0.04545 0.03529 -0.0453 0.5787 1.0000
5.000 0.7606 0.04612 0.03603 -0.0442 0.5678 1.0000
5.250 0.7959 0.04560 0.03562 -0.0434 0.5575 1.0000
5.500 0.7941 0.04834 0.03842 -0.0417 0.5441 1.0000
5.750 0.7958 0.05085 0.04099 -0.0403 0.5312 1.0000
6.000 0.8112 0.05210 0.04233 -0.0390 0.5191 1.0000
6.250 0.8679 0.04915 0.03954 -0.0378 0.5081 1.0000
6.500 0.9075 0.04761 0.03812 -0.0364 0.4945 1.0000
6.750 0.9362 0.04699 0.03760 -0.0348 0.4792 1.0000
7.000 0.9835 0.04445 0.03515 -0.0335 0.4629 1.0000
7.250 0.9991 0.04505 0.03586 -0.0315 0.4456 1.0000
7.500 1.0154 0.04564 0.03656 -0.0296 0.4280 1.0000
7.750 1.0369 0.04580 0.03685 -0.0278 0.4099 1.0000
8.000 1.0732 0.04469 0.03576 -0.0267 0.3901 1.0000
8.250 1.1164 0.04336 0.03432 -0.0261 0.3694 1.0000
8.500 1.1238 0.04510 0.03622 -0.0239 0.3513 1.0000
8.750 1.1353 0.04672 0.03795 -0.0220 0.3343 1.0000
9.000 1.1478 0.04842 0.03974 -0.0204 0.3188 1.0000
9.250 1.1623 0.05000 0.04139 -0.0189 0.3044 1.0000
9.500 1.1826 0.05125 0.04267 -0.0178 0.2908 1.0000
9.750 1.1400 0.05717 0.04895 -0.0139 0.2857 1.0000
10.000 1.1021 0.06292 0.05483 -0.0112 0.2813 1.0000
10.250 1.0516 0.07118 0.06311 -0.0107 0.2785 1.0000
10.500 0.8435 0.10849 0.09981 -0.0275 0.2895 1.0000
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Polar data table (+)
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