Curtis C-72 (curtisc72-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: Curtis C-72 (curtisc72-il) Reynolds number: 500,000 Max Cl/Cd: 103.37 at α=1.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-curtisc72-il-500000.txt Download as CSV file: xf-curtisc72-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: Curtis C-72
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.3746 0.08709 0.08478 -0.0431 1.0000 0.0378
-11.000 -0.3842 0.08395 0.08169 -0.0430 1.0000 0.0388
-10.500 -0.4699 0.03393 0.03040 -0.0975 0.9765 0.0356
-10.250 -0.4426 0.02964 0.02561 -0.1005 0.9733 0.0342
-10.000 -0.4124 0.02641 0.02194 -0.1034 0.9712 0.0343
-9.750 -0.3900 0.02339 0.01850 -0.1042 0.9650 0.0349
-9.500 -0.3622 0.02078 0.01565 -0.1054 0.9610 0.0355
-9.250 -0.3308 0.01920 0.01390 -0.1066 0.9581 0.0359
-9.000 -0.3039 0.01806 0.01264 -0.1066 0.9523 0.0363
-8.750 -0.2753 0.01705 0.01151 -0.1069 0.9468 0.0369
-8.500 -0.2450 0.01622 0.01058 -0.1074 0.9426 0.0376
-8.250 -0.2193 0.01552 0.00979 -0.1068 0.9349 0.0384
-8.000 -0.1913 0.01473 0.00890 -0.1067 0.9290 0.0389
-7.750 -0.1647 0.01404 0.00811 -0.1063 0.9219 0.0394
-7.500 -0.1379 0.01342 0.00740 -0.1059 0.9147 0.0399
-7.250 -0.1108 0.01289 0.00679 -0.1055 0.9077 0.0404
-7.000 -0.0843 0.01244 0.00627 -0.1050 0.8997 0.0409
-6.750 -0.0579 0.01180 0.00555 -0.1046 0.8926 0.0418
-6.500 -0.0321 0.01124 0.00496 -0.1040 0.8841 0.0431
-6.250 -0.0049 0.01088 0.00456 -0.1037 0.8769 0.0441
-6.000 0.0218 0.01056 0.00421 -0.1033 0.8681 0.0453
-5.750 0.0490 0.01029 0.00388 -0.1029 0.8597 0.0466
-5.500 0.0760 0.01004 0.00357 -0.1025 0.8497 0.0481
-5.250 0.1029 0.00976 0.00323 -0.1020 0.8391 0.0503
-5.000 0.1302 0.00952 0.00297 -0.1017 0.8289 0.0542
-4.750 0.1573 0.00931 0.00274 -0.1013 0.8175 0.0613
-4.500 0.1844 0.00902 0.00253 -0.1010 0.8067 0.0858
-4.250 0.2116 0.00872 0.00234 -0.1008 0.7974 0.1278
-4.000 0.2386 0.00842 0.00222 -0.1006 0.7875 0.1877
-3.750 0.2654 0.00810 0.00212 -0.1005 0.7779 0.2626
-3.500 0.2921 0.00780 0.00206 -0.1002 0.7681 0.3529
-3.250 0.3190 0.00762 0.00207 -0.1000 0.7577 0.4287
-3.000 0.3464 0.00755 0.00207 -0.0998 0.7483 0.4726
-2.750 0.3738 0.00752 0.00206 -0.0995 0.7380 0.5036
-2.500 0.4012 0.00749 0.00206 -0.0993 0.7275 0.5312
-2.250 0.4285 0.00748 0.00206 -0.0990 0.7172 0.5582
-2.000 0.4556 0.00744 0.00207 -0.0987 0.7066 0.5874
-1.750 0.4826 0.00739 0.00209 -0.0985 0.6963 0.6206
-1.500 0.5094 0.00736 0.00211 -0.0981 0.6859 0.6547
-1.250 0.5354 0.00725 0.00213 -0.0976 0.6744 0.7045
-1.000 0.5577 0.00693 0.00219 -0.0962 0.6630 0.8161
-0.750 0.6005 0.00675 0.00219 -0.0990 0.6508 1.0000
-0.500 0.6271 0.00687 0.00222 -0.0987 0.6390 1.0000
-0.250 0.6538 0.00697 0.00225 -0.0985 0.6260 1.0000
0.000 0.6804 0.00709 0.00230 -0.0982 0.6122 1.0000
0.250 0.7068 0.00722 0.00235 -0.0979 0.5977 1.0000
0.500 0.7332 0.00735 0.00242 -0.0976 0.5829 1.0000
0.750 0.7593 0.00751 0.00250 -0.0972 0.5668 1.0000
1.000 0.7851 0.00768 0.00258 -0.0968 0.5490 1.0000
1.250 0.8106 0.00788 0.00269 -0.0964 0.5300 1.0000
1.500 0.8361 0.00809 0.00281 -0.0960 0.5094 1.0000
1.750 0.8611 0.00833 0.00294 -0.0955 0.4862 1.0000
2.000 0.8856 0.00861 0.00311 -0.0950 0.4617 1.0000
2.250 0.9097 0.00892 0.00329 -0.0944 0.4355 1.0000
2.500 0.9340 0.00924 0.00348 -0.0939 0.4113 1.0000
2.750 0.9585 0.00955 0.00369 -0.0935 0.3917 1.0000
3.000 0.9835 0.00982 0.00390 -0.0931 0.3776 1.0000
3.250 1.0086 0.01009 0.00413 -0.0927 0.3660 1.0000
3.750 1.0587 0.01063 0.00460 -0.0921 0.3449 1.0000
4.000 1.0836 0.01090 0.00484 -0.0918 0.3355 1.0000
4.250 1.1085 0.01117 0.00510 -0.0914 0.3267 1.0000
4.500 1.1336 0.01142 0.00536 -0.0912 0.3188 1.0000
4.750 1.1581 0.01171 0.00563 -0.0908 0.3104 1.0000
5.000 1.1831 0.01195 0.00589 -0.0905 0.3024 1.0000
5.250 1.2068 0.01228 0.00619 -0.0900 0.2929 1.0000
5.500 1.2314 0.01252 0.00645 -0.0897 0.2807 1.0000
5.750 1.2548 0.01284 0.00673 -0.0893 0.2649 1.0000
6.000 1.2772 0.01322 0.00705 -0.0887 0.2470 1.0000
6.250 1.2995 0.01361 0.00738 -0.0880 0.2274 1.0000
6.500 1.3201 0.01411 0.00778 -0.0872 0.2045 1.0000
6.750 1.3391 0.01473 0.00827 -0.0861 0.1799 1.0000
7.000 1.3565 0.01543 0.00886 -0.0848 0.1578 1.0000
7.250 1.3741 0.01610 0.00945 -0.0836 0.1398 1.0000
7.500 1.3911 0.01678 0.01006 -0.0822 0.1250 1.0000
7.750 1.4067 0.01743 0.01067 -0.0806 0.1132 1.0000
8.000 1.4216 0.01810 0.01131 -0.0789 0.1029 1.0000
8.250 1.4358 0.01883 0.01200 -0.0772 0.0934 1.0000
8.500 1.4507 0.01950 0.01269 -0.0756 0.0845 1.0000
8.750 1.4638 0.02031 0.01347 -0.0739 0.0737 1.0000
9.000 1.4731 0.02137 0.01444 -0.0717 0.0577 1.0000
9.250 1.4772 0.02281 0.01575 -0.0691 0.0405 1.0000
9.500 1.4824 0.02423 0.01714 -0.0668 0.0331 1.0000
9.750 1.4870 0.02574 0.01867 -0.0645 0.0293 1.0000
10.000 1.4953 0.02703 0.02004 -0.0628 0.0271 1.0000
10.250 1.4995 0.02868 0.02173 -0.0610 0.0254 1.0000
10.500 1.5028 0.03048 0.02362 -0.0592 0.0240 1.0000
10.750 1.5091 0.03208 0.02533 -0.0579 0.0230 1.0000
11.000 1.5138 0.03390 0.02723 -0.0566 0.0220 1.0000
11.250 1.5155 0.03605 0.02945 -0.0554 0.0212 1.0000
11.500 1.5113 0.03888 0.03236 -0.0541 0.0204 1.0000
11.750 1.5098 0.04155 0.03514 -0.0532 0.0199 1.0000
12.000 1.5117 0.04397 0.03768 -0.0526 0.0194 1.0000
12.250 1.5114 0.04671 0.04053 -0.0521 0.0189 1.0000
12.500 1.5095 0.04971 0.04363 -0.0518 0.0184 1.0000
12.750 1.5064 0.05297 0.04700 -0.0517 0.0180 1.0000
13.000 1.5021 0.05650 0.05063 -0.0518 0.0177 1.0000
13.250 1.4962 0.06034 0.05456 -0.0520 0.0174 1.0000
13.500 1.4880 0.06459 0.05890 -0.0525 0.0171 1.0000
13.750 1.4776 0.06923 0.06364 -0.0531 0.0168 1.0000
14.000 1.4648 0.07423 0.06874 -0.0539 0.0166 1.0000
14.250 1.4568 0.07871 0.07332 -0.0547 0.0164 1.0000
14.500 1.4523 0.08285 0.07758 -0.0557 0.0162 1.0000
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