Curtis C-72 (curtisc72-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: Curtis C-72 (curtisc72-il) Reynolds number: 200,000 Max Cl/Cd: 76.3 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-curtisc72-il-200000.txt Download as CSV file: xf-curtisc72-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3609 0.08884 0.08535 -0.0387 1.0000 0.0745
-10.250 -0.3749 0.08698 0.08358 -0.0367 1.0000 0.0759
-10.000 -0.3977 0.08566 0.08235 -0.0335 1.0000 0.0770
-9.750 -0.4265 0.08471 0.08150 -0.0294 1.0000 0.0775
-9.500 -0.4457 0.06976 0.06642 -0.0569 0.9913 0.0816
-9.250 -0.4213 0.06853 0.06529 -0.0541 0.9887 0.0827
-9.000 -0.3948 0.06742 0.06418 -0.0533 0.9856 0.0849
-8.750 -0.3683 0.06175 0.05840 -0.0623 0.9793 0.0899
-8.500 -0.3434 0.05142 0.04765 -0.0773 0.9717 0.0970
-8.250 -0.3247 0.03606 0.03087 -0.0863 0.9623 0.0671
-8.000 -0.2916 0.03165 0.02608 -0.0897 0.9588 0.0651
-7.750 -0.2596 0.02747 0.02130 -0.0919 0.9545 0.0621
-7.500 -0.2285 0.02465 0.01793 -0.0930 0.9486 0.0609
-7.250 -0.1903 0.02286 0.01583 -0.0952 0.9453 0.0612
-7.000 -0.1491 0.02165 0.01447 -0.0979 0.9431 0.0631
-6.750 -0.1184 0.02059 0.01323 -0.0984 0.9364 0.0643
-6.500 -0.0808 0.01945 0.01192 -0.1001 0.9323 0.0655
-6.250 -0.0411 0.01844 0.01079 -0.1021 0.9294 0.0670
-6.000 -0.0011 0.01752 0.00977 -0.1042 0.9269 0.0688
-5.750 0.0240 0.01668 0.00900 -0.1036 0.9178 0.0722
-5.500 0.0601 0.01602 0.00835 -0.1050 0.9137 0.0768
-5.250 0.0907 0.01544 0.00773 -0.1052 0.9072 0.0814
-5.000 0.1205 0.01474 0.00711 -0.1054 0.9001 0.0905
-4.750 0.1540 0.01387 0.00637 -0.1062 0.8956 0.1201
-4.500 0.1782 0.01310 0.00602 -0.1056 0.8853 0.2042
-4.250 0.2085 0.01225 0.00569 -0.1059 0.8787 0.3481
-4.000 0.2329 0.01192 0.00561 -0.1048 0.8668 0.4404
-3.750 0.2593 0.01170 0.00549 -0.1040 0.8562 0.5010
-3.500 0.2874 0.01148 0.00534 -0.1034 0.8481 0.5500
-3.250 0.3122 0.01137 0.00532 -0.1024 0.8378 0.5912
-3.000 0.3402 0.01117 0.00516 -0.1019 0.8303 0.6284
-2.750 0.3651 0.01103 0.00510 -0.1009 0.8196 0.6613
-2.500 0.3910 0.01083 0.00499 -0.1001 0.8106 0.6984
-2.250 0.4155 0.01053 0.00488 -0.0988 0.8013 0.7544
-2.000 0.4450 0.01010 0.00483 -0.0980 0.7913 0.9025
-1.750 0.4915 0.00997 0.00457 -0.1016 0.7824 1.0000
-1.500 0.5181 0.01003 0.00451 -0.1013 0.7710 1.0000
-1.250 0.5451 0.01008 0.00446 -0.1010 0.7599 1.0000
-1.000 0.5727 0.01013 0.00437 -0.1008 0.7492 1.0000
-0.750 0.5995 0.01020 0.00434 -0.1004 0.7373 1.0000
-0.500 0.6259 0.01029 0.00435 -0.0999 0.7250 1.0000
-0.250 0.6526 0.01038 0.00436 -0.0996 0.7127 1.0000
0.000 0.6793 0.01047 0.00436 -0.0992 0.7001 1.0000
0.250 0.7060 0.01058 0.00436 -0.0988 0.6869 1.0000
0.500 0.7320 0.01069 0.00441 -0.0983 0.6727 1.0000
0.750 0.7579 0.01082 0.00448 -0.0978 0.6578 1.0000
1.000 0.7836 0.01096 0.00454 -0.0973 0.6419 1.0000
1.250 0.8092 0.01111 0.00462 -0.0967 0.6252 1.0000
1.500 0.8346 0.01129 0.00471 -0.0961 0.6079 1.0000
1.750 0.8593 0.01147 0.00484 -0.0955 0.5884 1.0000
2.000 0.8838 0.01169 0.00499 -0.0948 0.5679 1.0000
2.250 0.9082 0.01194 0.00514 -0.0941 0.5473 1.0000
2.500 0.9322 0.01223 0.00532 -0.0934 0.5264 1.0000
2.750 0.9560 0.01253 0.00555 -0.0927 0.5052 1.0000
3.000 0.9796 0.01287 0.00578 -0.0920 0.4854 1.0000
3.250 1.0029 0.01323 0.00603 -0.0912 0.4663 1.0000
3.500 1.0260 0.01359 0.00631 -0.0905 0.4471 1.0000
3.750 1.0492 0.01395 0.00661 -0.0898 0.4302 1.0000
4.000 1.0729 0.01435 0.00694 -0.0893 0.4165 1.0000
4.250 1.0966 0.01473 0.00730 -0.0887 0.4037 1.0000
4.500 1.1205 0.01510 0.00769 -0.0882 0.3919 1.0000
4.750 1.1442 0.01552 0.00809 -0.0877 0.3809 1.0000
5.000 1.1674 0.01597 0.00848 -0.0871 0.3700 1.0000
5.250 1.1903 0.01634 0.00892 -0.0865 0.3584 1.0000
5.500 1.2131 0.01675 0.00937 -0.0859 0.3473 1.0000
5.750 1.2355 0.01722 0.00982 -0.0852 0.3369 1.0000
6.000 1.2572 0.01765 0.01028 -0.0844 0.3255 1.0000
6.250 1.2782 0.01806 0.01078 -0.0836 0.3131 1.0000
6.500 1.2979 0.01850 0.01125 -0.0825 0.2993 1.0000
6.750 1.3155 0.01892 0.01169 -0.0811 0.2820 1.0000
7.000 1.3312 0.01939 0.01213 -0.0794 0.2625 1.0000
7.250 1.3471 0.01987 0.01264 -0.0779 0.2409 1.0000
7.500 1.3612 0.02049 0.01324 -0.0760 0.2198 1.0000
7.750 1.3722 0.02124 0.01393 -0.0738 0.1995 1.0000
8.000 1.3826 0.02212 0.01475 -0.0715 0.1801 1.0000
8.250 1.3916 0.02313 0.01571 -0.0693 0.1637 1.0000
8.500 1.4004 0.02421 0.01676 -0.0671 0.1498 1.0000
8.750 1.4090 0.02534 0.01789 -0.0651 0.1373 1.0000
9.000 1.4170 0.02656 0.01911 -0.0631 0.1256 1.0000
9.250 1.4238 0.02790 0.02045 -0.0612 0.1140 1.0000
9.500 1.4289 0.02941 0.02198 -0.0593 0.1017 1.0000
9.750 1.4317 0.03119 0.02376 -0.0573 0.0875 1.0000
10.000 1.4304 0.03339 0.02592 -0.0553 0.0733 1.0000
10.250 1.4278 0.03583 0.02833 -0.0534 0.0622 1.0000
10.500 1.4256 0.03834 0.03087 -0.0518 0.0550 1.0000
10.750 1.4203 0.04125 0.03376 -0.0504 0.0506 1.0000
11.000 1.4199 0.04381 0.03645 -0.0493 0.0471 1.0000
11.250 1.4173 0.04668 0.03937 -0.0485 0.0445 1.0000
11.500 1.4092 0.05017 0.04288 -0.0476 0.0427 1.0000
11.750 1.4079 0.05308 0.04594 -0.0470 0.0409 1.0000
12.000 1.4063 0.05609 0.04906 -0.0466 0.0392 1.0000
12.250 1.4036 0.05929 0.05233 -0.0464 0.0377 1.0000
12.500 1.3995 0.06267 0.05576 -0.0463 0.0365 1.0000
12.750 1.3958 0.06593 0.05902 -0.0456 0.0353 1.0000
13.000 1.3958 0.06901 0.06226 -0.0456 0.0345 1.0000
13.250 1.3957 0.07211 0.06549 -0.0455 0.0335 1.0000
13.500 1.3958 0.07521 0.06870 -0.0455 0.0327 1.0000
13.750 1.3960 0.07830 0.07188 -0.0455 0.0319 1.0000
14.000 1.3967 0.08130 0.07495 -0.0456 0.0311 1.0000
14.250 1.3995 0.08389 0.07754 -0.0452 0.0303 1.0000
14.500 1.4029 0.08636 0.08005 -0.0443 0.0294 1.0000
14.750 1.3982 0.09052 0.08441 -0.0453 0.0290 1.0000
15.000 1.3928 0.09482 0.08892 -0.0465 0.0285 1.0000
15.250 1.3872 0.09921 0.09350 -0.0478 0.0281 1.0000
15.500 1.3811 0.10378 0.09825 -0.0492 0.0277 1.0000
15.750 1.3744 0.10854 0.10318 -0.0508 0.0274 1.0000
16.000 1.3665 0.11361 0.10844 -0.0528 0.0271 1.0000
16.250 1.3569 0.11911 0.11412 -0.0552 0.0269 1.0000
16.500 1.3456 0.12510 0.12031 -0.0581 0.0267 1.0000
16.750 1.3318 0.13181 0.12722 -0.0617 0.0266 1.0000
17.000 1.3143 0.13961 0.13525 -0.0662 0.0267 1.0000
17.250 1.2914 0.14907 0.14496 -0.0720 0.0268 1.0000
17.500 1.2585 0.16163 0.15781 -0.0802 0.0273 1.0000
17.750 1.2040 0.18163 0.17813 -0.0933 0.0283 1.0000
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Polar data table (+)
Polar graphs
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