Curtis C-72 (curtisc72-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: Curtis C-72 (curtisc72-il) Reynolds number: 100,000 Max Cl/Cd: 54.71 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-curtisc72-il-100000.txt Download as CSV file: xf-curtisc72-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3405 0.09651 0.09153 -0.0350 1.0000 0.1319
-10.250 -0.3542 0.09472 0.08985 -0.0348 1.0000 0.1362
-10.000 -0.3978 0.09473 0.09007 -0.0333 1.0000 0.1382
-9.750 -0.4461 0.09377 0.08929 -0.0360 1.0000 0.1390
-9.500 -0.4201 0.08970 0.08522 -0.0288 1.0000 0.1410
-9.250 -0.4112 0.08767 0.08321 -0.0248 1.0000 0.1438
-9.000 -0.4193 0.08602 0.08163 -0.0225 1.0000 0.1470
-8.750 -0.4381 0.08410 0.07980 -0.0226 1.0000 0.1514
-8.500 -0.4652 0.07973 0.07547 -0.0293 1.0000 0.1560
-8.250 -0.4565 0.07849 0.07430 -0.0227 1.0000 0.1586
-8.000 -0.4555 0.07672 0.07256 -0.0207 1.0000 0.1638
-7.750 -0.4629 0.07206 0.06786 -0.0269 1.0000 0.1729
-7.500 -0.4571 0.07068 0.06652 -0.0229 1.0000 0.1766
-7.250 -0.4271 0.06577 0.06150 -0.0312 0.9944 0.1907
-7.000 -0.3684 0.04243 0.03634 -0.0596 0.9892 0.1113
-6.750 -0.3266 0.03781 0.03115 -0.0642 0.9848 0.1031
-6.500 -0.2848 0.03358 0.02613 -0.0683 0.9804 0.0984
-6.250 -0.2431 0.03089 0.02264 -0.0713 0.9750 0.0958
-6.000 -0.1986 0.02901 0.02039 -0.0748 0.9708 0.0965
-5.750 -0.1642 0.02783 0.01911 -0.0765 0.9635 0.0997
-5.500 -0.1210 0.02676 0.01783 -0.0795 0.9583 0.1040
-5.250 -0.0848 0.02583 0.01665 -0.0810 0.9512 0.1072
-5.000 -0.0441 0.02469 0.01551 -0.0835 0.9454 0.1124
-4.750 -0.0052 0.02405 0.01484 -0.0855 0.9389 0.1226
-4.500 0.0314 0.02324 0.01417 -0.0873 0.9315 0.1397
-4.250 0.0777 0.02195 0.01333 -0.0909 0.9273 0.1992
-4.000 0.1073 0.02076 0.01328 -0.0919 0.9184 0.4057
-3.750 0.1475 0.02053 0.01344 -0.0936 0.9122 0.5557
-3.500 0.1729 0.02045 0.01358 -0.0926 0.9014 0.6316
-3.250 0.2187 0.01993 0.01318 -0.0947 0.8955 0.7010
-3.000 0.2450 0.01958 0.01299 -0.0935 0.8833 0.7580
-2.750 0.2767 0.01898 0.01269 -0.0924 0.8748 0.8599
-2.500 0.3331 0.01853 0.01213 -0.0975 0.8669 1.0000
-2.250 0.3687 0.01850 0.01189 -0.0990 0.8574 1.0000
-2.000 0.4081 0.01830 0.01150 -0.1008 0.8495 1.0000
-1.750 0.4375 0.01833 0.01140 -0.1009 0.8386 1.0000
-1.500 0.4773 0.01801 0.01094 -0.1024 0.8319 1.0000
-1.250 0.5035 0.01807 0.01090 -0.1019 0.8196 1.0000
-1.000 0.5341 0.01798 0.01072 -0.1019 0.8094 1.0000
-0.750 0.5685 0.01770 0.01035 -0.1023 0.8006 1.0000
-0.500 0.5950 0.01771 0.01029 -0.1016 0.7880 1.0000
-0.250 0.6238 0.01763 0.01015 -0.1013 0.7764 1.0000
0.000 0.6585 0.01728 0.00971 -0.1016 0.7673 1.0000
0.250 0.6847 0.01727 0.00965 -0.1008 0.7532 1.0000
0.500 0.7116 0.01725 0.00958 -0.1001 0.7392 1.0000
0.750 0.7391 0.01722 0.00950 -0.0995 0.7248 1.0000
1.000 0.7667 0.01718 0.00941 -0.0989 0.7098 1.0000
1.250 0.7942 0.01717 0.00934 -0.0982 0.6940 1.0000
1.500 0.8214 0.01719 0.00930 -0.0976 0.6775 1.0000
1.750 0.8483 0.01725 0.00929 -0.0970 0.6603 1.0000
2.000 0.8753 0.01733 0.00931 -0.0964 0.6426 1.0000
2.250 0.9022 0.01746 0.00934 -0.0958 0.6247 1.0000
2.500 0.9274 0.01770 0.00952 -0.0951 0.6059 1.0000
2.750 0.9519 0.01798 0.00977 -0.0943 0.5868 1.0000
3.000 0.9768 0.01829 0.01002 -0.0936 0.5688 1.0000
3.250 1.0017 0.01862 0.01029 -0.0929 0.5514 1.0000
3.500 1.0266 0.01898 0.01062 -0.0923 0.5349 1.0000
3.750 1.0511 0.01936 0.01096 -0.0917 0.5188 1.0000
4.000 1.0752 0.01974 0.01130 -0.0910 0.5028 1.0000
4.250 1.0988 0.02011 0.01163 -0.0902 0.4865 1.0000
4.500 1.1222 0.02051 0.01201 -0.0894 0.4707 1.0000
4.750 1.1453 0.02095 0.01244 -0.0887 0.4557 1.0000
5.000 1.1684 0.02143 0.01293 -0.0880 0.4416 1.0000
5.250 1.1916 0.02194 0.01346 -0.0873 0.4279 1.0000
5.500 1.2147 0.02247 0.01398 -0.0866 0.4143 1.0000
5.750 1.2379 0.02302 0.01451 -0.0859 0.4008 1.0000
6.000 1.2605 0.02358 0.01507 -0.0852 0.3866 1.0000
6.250 1.2810 0.02417 0.01572 -0.0841 0.3715 1.0000
6.500 1.3010 0.02479 0.01637 -0.0830 0.3559 1.0000
6.750 1.3205 0.02545 0.01705 -0.0819 0.3398 1.0000
7.000 1.3381 0.02616 0.01779 -0.0804 0.3227 1.0000
7.250 1.3526 0.02688 0.01862 -0.0785 0.3042 1.0000
7.500 1.3649 0.02754 0.01934 -0.0763 0.2847 1.0000
7.750 1.3751 0.02813 0.01994 -0.0738 0.2653 1.0000
8.000 1.3834 0.02875 0.02052 -0.0712 0.2470 1.0000
8.250 1.3891 0.02953 0.02134 -0.0682 0.2292 1.0000
8.500 1.3931 0.03041 0.02228 -0.0651 0.2130 1.0000
8.750 1.3964 0.03145 0.02333 -0.0620 0.1981 1.0000
9.000 1.3992 0.03268 0.02456 -0.0592 0.1840 1.0000
9.250 1.4012 0.03411 0.02597 -0.0566 0.1705 1.0000
9.500 1.4017 0.03575 0.02760 -0.0540 0.1573 1.0000
9.750 1.4006 0.03765 0.02947 -0.0516 0.1441 1.0000
10.000 1.3974 0.03984 0.03165 -0.0493 0.1308 1.0000
10.250 1.3926 0.04233 0.03411 -0.0471 0.1177 1.0000
10.500 1.3881 0.04503 0.03674 -0.0452 0.1054 1.0000
10.750 1.3833 0.04784 0.03967 -0.0435 0.0952 1.0000
11.000 1.3814 0.05067 0.04256 -0.0420 0.0867 1.0000
11.250 1.3843 0.05319 0.04495 -0.0407 0.0798 1.0000
11.500 1.3840 0.05601 0.04800 -0.0396 0.0747 1.0000
11.750 1.3964 0.05807 0.04983 -0.0385 0.0695 1.0000
12.000 1.3927 0.06123 0.05335 -0.0376 0.0667 1.0000
12.250 1.3921 0.06418 0.05649 -0.0369 0.0637 1.0000
12.500 1.3985 0.06651 0.05878 -0.0363 0.0607 1.0000
12.750 1.4047 0.06952 0.06189 -0.0354 0.0586 1.0000
13.000 1.3983 0.07342 0.06610 -0.0350 0.0574 1.0000
13.250 1.3902 0.07759 0.07055 -0.0349 0.0563 1.0000
13.500 1.3802 0.08202 0.07523 -0.0352 0.0554 1.0000
13.750 1.3688 0.08671 0.08016 -0.0358 0.0546 1.0000
14.000 1.3552 0.09182 0.08549 -0.0369 0.0539 1.0000
14.250 1.3388 0.09753 0.09144 -0.0387 0.0534 1.0000
14.500 1.3185 0.10414 0.09829 -0.0412 0.0532 1.0000
14.750 1.2810 0.11429 0.10880 -0.0464 0.0541 1.0000
15.000 1.2288 0.12863 0.12351 -0.0550 0.0560 1.0000
15.250 1.1803 0.14412 0.13922 -0.0646 0.0578 1.0000
15.500 1.1389 0.15983 0.15500 -0.0740 0.0592 1.0000
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Polar data table (+)
Polar graphs
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