Curtis C-72 (curtisc72-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: Curtis C-72 (curtisc72-il) Reynolds number: 100,000 Max Cl/Cd: 56.49 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-curtisc72-il-100000-n5.txt Download as CSV file: xf-curtisc72-il-100000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.3791 0.09085 0.08565 -0.0446 1.0000 0.0492
-11.000 -0.3883 0.08705 0.08193 -0.0454 1.0000 0.0494
-10.750 -0.4011 0.08349 0.07847 -0.0456 1.0000 0.0494
-10.500 -0.4190 0.08049 0.07558 -0.0445 1.0000 0.0493
-10.250 -0.4416 0.07783 0.07304 -0.0428 1.0000 0.0491
-10.000 -0.4616 0.07400 0.06930 -0.0432 1.0000 0.0488
-9.750 -0.4610 0.06197 0.05710 -0.0582 0.9922 0.0480
-9.500 -0.4513 0.05042 0.04500 -0.0713 0.9822 0.0476
-9.250 -0.4320 0.04358 0.03755 -0.0777 0.9746 0.0481
-9.000 -0.4095 0.03874 0.03206 -0.0814 0.9673 0.0495
-8.750 -0.3806 0.03487 0.02752 -0.0846 0.9621 0.0504
-8.500 -0.3533 0.03210 0.02421 -0.0861 0.9559 0.0509
-8.250 -0.3225 0.02987 0.02159 -0.0877 0.9506 0.0515
-8.000 -0.2877 0.02818 0.01970 -0.0898 0.9472 0.0524
-7.750 -0.2601 0.02711 0.01852 -0.0902 0.9401 0.0539
-7.500 -0.2262 0.02598 0.01719 -0.0917 0.9353 0.0559
-7.250 -0.1896 0.02470 0.01568 -0.0936 0.9321 0.0576
-7.000 -0.1620 0.02367 0.01446 -0.0936 0.9246 0.0587
-6.750 -0.1284 0.02265 0.01326 -0.0946 0.9196 0.0601
-6.500 -0.0928 0.02166 0.01223 -0.0961 0.9160 0.0619
-6.250 -0.0667 0.02104 0.01161 -0.0959 0.9076 0.0639
-6.000 -0.0333 0.02041 0.01094 -0.0969 0.9025 0.0679
-5.750 -0.0023 0.01985 0.01030 -0.0973 0.8964 0.0723
-5.500 0.0264 0.01924 0.00972 -0.0975 0.8890 0.0771
-5.250 0.0604 0.01866 0.00904 -0.0985 0.8842 0.0852
-5.000 0.0863 0.01816 0.00860 -0.0982 0.8753 0.0974
-4.750 0.1182 0.01756 0.00810 -0.0989 0.8694 0.1220
-4.500 0.1455 0.01709 0.00781 -0.0989 0.8612 0.1633
-4.250 0.1754 0.01650 0.00752 -0.0993 0.8543 0.2374
-4.000 0.2021 0.01593 0.00749 -0.0993 0.8463 0.3632
-3.750 0.2301 0.01566 0.00748 -0.0990 0.8385 0.4617
-3.500 0.2571 0.01552 0.00740 -0.0984 0.8296 0.5109
-3.250 0.2868 0.01528 0.00715 -0.0982 0.8204 0.5494
-3.000 0.3124 0.01508 0.00701 -0.0972 0.8076 0.5885
-2.750 0.3383 0.01483 0.00685 -0.0962 0.7954 0.6373
-2.500 0.3648 0.01453 0.00667 -0.0952 0.7850 0.6899
-2.250 0.3897 0.01425 0.00655 -0.0939 0.7747 0.7472
-2.000 0.4185 0.01389 0.00647 -0.0931 0.7645 0.8570
-1.750 0.4627 0.01371 0.00619 -0.0961 0.7549 1.0000
-1.500 0.4898 0.01378 0.00612 -0.0959 0.7434 1.0000
-1.250 0.5170 0.01386 0.00607 -0.0957 0.7319 1.0000
-1.000 0.5450 0.01392 0.00600 -0.0956 0.7210 1.0000
-0.750 0.5726 0.01399 0.00595 -0.0954 0.7094 1.0000
-0.500 0.5990 0.01411 0.00598 -0.0950 0.6966 1.0000
-0.250 0.6257 0.01422 0.00601 -0.0947 0.6840 1.0000
0.000 0.6525 0.01434 0.00603 -0.0943 0.6712 1.0000
0.250 0.6793 0.01446 0.00606 -0.0940 0.6580 1.0000
0.500 0.7059 0.01460 0.00611 -0.0936 0.6444 1.0000
0.750 0.7318 0.01476 0.00621 -0.0931 0.6297 1.0000
1.000 0.7575 0.01493 0.00632 -0.0927 0.6145 1.0000
1.250 0.7831 0.01512 0.00645 -0.0922 0.5987 1.0000
1.500 0.8085 0.01533 0.00659 -0.0916 0.5827 1.0000
1.750 0.8337 0.01555 0.00675 -0.0911 0.5663 1.0000
2.000 0.8587 0.01579 0.00694 -0.0905 0.5495 1.0000
2.250 0.8833 0.01606 0.00715 -0.0900 0.5323 1.0000
2.500 0.9077 0.01635 0.00739 -0.0894 0.5151 1.0000
2.750 0.9319 0.01667 0.00766 -0.0887 0.4982 1.0000
3.000 0.9558 0.01701 0.00795 -0.0881 0.4815 1.0000
3.250 0.9796 0.01737 0.00827 -0.0875 0.4656 1.0000
3.500 1.0031 0.01776 0.00862 -0.0868 0.4500 1.0000
3.750 1.0264 0.01817 0.00898 -0.0862 0.4352 1.0000
4.000 1.0494 0.01859 0.00936 -0.0855 0.4208 1.0000
4.250 1.0716 0.01904 0.00978 -0.0847 0.4056 1.0000
4.500 1.0934 0.01950 0.01020 -0.0838 0.3902 1.0000
4.750 1.1149 0.01998 0.01065 -0.0830 0.3757 1.0000
5.000 1.1365 0.02046 0.01115 -0.0822 0.3622 1.0000
5.250 1.1581 0.02096 0.01170 -0.0814 0.3502 1.0000
5.500 1.1794 0.02148 0.01224 -0.0806 0.3391 1.0000
5.750 1.2001 0.02202 0.01280 -0.0797 0.3282 1.0000
6.000 1.2209 0.02255 0.01344 -0.0788 0.3170 1.0000
6.250 1.2408 0.02311 0.01407 -0.0779 0.3060 1.0000
6.500 1.2595 0.02371 0.01470 -0.0767 0.2945 1.0000
6.750 1.2774 0.02431 0.01539 -0.0755 0.2818 1.0000
7.000 1.2946 0.02493 0.01612 -0.0742 0.2688 1.0000
7.250 1.3107 0.02558 0.01689 -0.0727 0.2557 1.0000
7.500 1.3251 0.02629 0.01768 -0.0711 0.2417 1.0000
7.750 1.3366 0.02706 0.01850 -0.0690 0.2270 1.0000
8.000 1.3462 0.02793 0.01940 -0.0668 0.2110 1.0000
8.250 1.3538 0.02897 0.02042 -0.0645 0.1944 1.0000
8.500 1.3592 0.03020 0.02162 -0.0621 0.1779 1.0000
8.750 1.3634 0.03160 0.02297 -0.0599 0.1625 1.0000
9.000 1.3676 0.03311 0.02447 -0.0579 0.1486 1.0000
9.250 1.3719 0.03471 0.02609 -0.0561 0.1361 1.0000
9.500 1.3761 0.03640 0.02783 -0.0544 0.1252 1.0000
9.750 1.3791 0.03824 0.02974 -0.0529 0.1161 1.0000
10.000 1.3797 0.04035 0.03190 -0.0514 0.1079 1.0000
10.250 1.3824 0.04241 0.03407 -0.0502 0.0993 1.0000
10.500 1.3812 0.04489 0.03661 -0.0491 0.0921 1.0000
10.750 1.3800 0.04749 0.03932 -0.0482 0.0844 1.0000
11.000 1.3775 0.05034 0.04228 -0.0475 0.0773 1.0000
11.250 1.3715 0.05368 0.04569 -0.0471 0.0709 1.0000
11.500 1.3675 0.05696 0.04912 -0.0468 0.0641 1.0000
11.750 1.3583 0.06097 0.05317 -0.0469 0.0595 1.0000
12.000 1.3518 0.06484 0.05720 -0.0471 0.0545 1.0000
12.250 1.3412 0.06941 0.06184 -0.0478 0.0512 1.0000
12.500 1.3318 0.07398 0.06652 -0.0486 0.0481 1.0000
12.750 1.3220 0.07878 0.07147 -0.0496 0.0455 1.0000
13.000 1.3104 0.08402 0.07680 -0.0510 0.0435 1.0000
13.250 1.2984 0.08943 0.08226 -0.0526 0.0420 1.0000
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Polar data table (+)
Polar graphs
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