CLARK-Y 11.7% smoothed (clarkysm-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: CLARK-Y 11.7% smoothed (clarkysm-il) Reynolds number: 50,000 Max Cl/Cd: 29.99 at α=10° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-clarkysm-il-50000.txt Download as CSV file: xf-clarkysm-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: CLARK-Y 11.7% smoothed
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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3501 0.11006 0.10325 -0.0289 1.0000 0.2480
-8.500 -0.3261 0.10484 0.09801 -0.0270 1.0000 0.2573
-8.250 -0.3542 0.10506 0.09842 -0.0258 1.0000 0.2641
-8.000 -0.3350 0.10065 0.09401 -0.0238 1.0000 0.2764
-7.750 -0.3749 0.10159 0.09519 -0.0214 1.0000 0.2809
-7.500 -0.3551 0.09731 0.09092 -0.0192 1.0000 0.2951
-7.250 -0.3530 0.09441 0.08809 -0.0169 1.0000 0.3045
-7.000 -0.3875 0.09474 0.08860 -0.0130 1.0000 0.3129
-6.750 -0.3736 0.09100 0.08489 -0.0108 1.0000 0.3240
-6.500 -0.4246 0.09219 0.08631 -0.0058 1.0000 0.3299
-6.250 -0.4090 0.08848 0.08262 -0.0032 1.0000 0.3433
-5.750 -0.4398 0.08504 0.07941 0.0033 1.0000 0.3662
-5.500 -0.4555 0.08348 0.07794 0.0064 1.0000 0.3814
-5.000 -0.4520 0.07885 0.07341 0.0143 1.0000 0.4251
-4.750 -0.4712 0.06046 0.05384 -0.0243 1.0000 0.2001
-4.500 -0.4588 0.05675 0.05017 -0.0231 1.0000 0.1929
-4.250 -0.4389 0.04907 0.04141 -0.0277 1.0000 0.1676
-4.000 -0.4225 0.04581 0.03786 -0.0274 1.0000 0.1657
-3.750 -0.4045 0.04280 0.03431 -0.0272 1.0000 0.1669
-3.500 -0.3856 0.04014 0.03109 -0.0267 1.0000 0.1692
-3.250 -0.3682 0.03839 0.02929 -0.0258 1.0000 0.1740
-3.000 -0.3488 0.03677 0.02725 -0.0250 1.0000 0.1812
-2.750 -0.3292 0.03517 0.02534 -0.0241 1.0000 0.1876
-2.500 -0.3097 0.03414 0.02402 -0.0232 1.0000 0.1987
-2.250 -0.2906 0.03310 0.02290 -0.0223 1.0000 0.2087
-2.000 -0.2710 0.03228 0.02192 -0.0214 1.0000 0.2221
-1.750 -0.2505 0.03159 0.02112 -0.0207 1.0000 0.2379
-1.500 -0.2304 0.03105 0.02055 -0.0200 1.0000 0.2578
-1.250 -0.2104 0.03060 0.02005 -0.0192 1.0000 0.2829
-1.000 -0.1863 0.03020 0.01975 -0.0191 1.0000 0.3201
-0.750 -0.1619 0.02968 0.01956 -0.0191 1.0000 0.3851
-0.500 -0.0969 0.02747 0.01945 -0.0252 0.9967 1.0000
-0.250 -0.0426 0.02910 0.02042 -0.0314 0.9824 1.0000
0.000 0.0017 0.03030 0.02122 -0.0357 0.9676 1.0000
0.250 0.0438 0.03141 0.02201 -0.0395 0.9524 1.0000
0.500 0.0843 0.03245 0.02279 -0.0429 0.9369 1.0000
0.750 0.1237 0.03342 0.02353 -0.0460 0.9210 1.0000
1.000 0.1623 0.03432 0.02424 -0.0487 0.9045 1.0000
1.250 0.2000 0.03516 0.02492 -0.0512 0.8880 1.0000
1.500 0.2372 0.03594 0.02557 -0.0534 0.8713 1.0000
1.750 0.2740 0.03666 0.02619 -0.0554 0.8546 1.0000
2.000 0.3100 0.03734 0.02677 -0.0571 0.8381 1.0000
2.250 0.3461 0.03795 0.02730 -0.0587 0.8215 1.0000
2.500 0.3818 0.03850 0.02780 -0.0601 0.8050 1.0000
2.750 0.4173 0.03898 0.02825 -0.0614 0.7886 1.0000
3.000 0.4512 0.03945 0.02869 -0.0623 0.7725 1.0000
3.250 0.4857 0.03982 0.02905 -0.0631 0.7564 1.0000
3.500 0.5187 0.04018 0.02942 -0.0636 0.7405 1.0000
3.750 0.5508 0.04051 0.02976 -0.0639 0.7247 1.0000
4.000 0.5820 0.04082 0.03009 -0.0640 0.7091 1.0000
4.250 0.6110 0.04119 0.03049 -0.0638 0.6937 1.0000
4.500 0.6382 0.04162 0.03096 -0.0633 0.6785 1.0000
4.750 0.6633 0.04216 0.03153 -0.0626 0.6636 1.0000
5.000 0.6851 0.04290 0.03230 -0.0617 0.6490 1.0000
5.250 0.7056 0.04374 0.03319 -0.0606 0.6349 1.0000
5.500 0.7273 0.04457 0.03408 -0.0597 0.6219 1.0000
5.750 0.7912 0.04289 0.03253 -0.0622 0.6138 1.0000
6.000 0.7932 0.04484 0.03450 -0.0595 0.5996 1.0000
6.250 0.7869 0.04761 0.03731 -0.0568 0.5858 1.0000
6.500 0.7817 0.05065 0.04037 -0.0547 0.5730 1.0000
6.750 0.8575 0.04766 0.03757 -0.0568 0.5666 1.0000
7.000 0.8206 0.05307 0.04295 -0.0530 0.5527 1.0000
7.250 0.7919 0.05842 0.04827 -0.0509 0.5409 1.0000
7.500 0.8203 0.05903 0.04899 -0.0504 0.5320 1.0000
7.750 0.8132 0.06269 0.05269 -0.0493 0.5218 1.0000
8.000 0.7957 0.06734 0.05734 -0.0482 0.5122 1.0000
8.250 0.8413 0.06636 0.05656 -0.0475 0.5019 1.0000
8.500 0.8187 0.07142 0.06162 -0.0465 0.4910 1.0000
8.750 0.8164 0.07453 0.06478 -0.0455 0.4788 1.0000
9.000 0.8421 0.07454 0.06492 -0.0438 0.4622 1.0000
9.250 1.2049 0.04164 0.03260 -0.0496 0.4082 1.0000
9.500 1.2113 0.04245 0.03353 -0.0461 0.3875 1.0000
9.750 1.2404 0.04182 0.03283 -0.0444 0.3583 1.0000
10.000 1.2597 0.04200 0.03287 -0.0419 0.3282 1.0000
10.250 1.2762 0.04262 0.03330 -0.0393 0.2989 1.0000
10.500 1.2753 0.04427 0.03501 -0.0353 0.2781 1.0000
10.750 1.2884 0.04561 0.03627 -0.0329 0.2581 1.0000
11.000 1.2988 0.04713 0.03777 -0.0305 0.2420 1.0000
11.250 1.2938 0.04938 0.04020 -0.0267 0.2313 1.0000
11.500 1.3008 0.05136 0.04224 -0.0243 0.2205 1.0000
11.750 1.3187 0.05302 0.04385 -0.0231 0.2091 1.0000
12.000 1.2941 0.05616 0.04733 -0.0180 0.2054 1.0000
12.250 1.3170 0.05773 0.04882 -0.0174 0.1950 1.0000
12.500 1.2863 0.06159 0.05301 -0.0129 0.1933 1.0000
12.750 1.2519 0.06630 0.05801 -0.0097 0.1923 1.0000
13.000 1.2085 0.07250 0.06444 -0.0080 0.1927 1.0000
13.250 1.1551 0.08107 0.07317 -0.0085 0.1943 1.0000
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Polar data table (+)
Polar graphs
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