Curtis C-72 (curtisc72-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: Curtis C-72 (curtisc72-il) Reynolds number: 1,000,000 Max Cl/Cd: 121 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-curtisc72-il-1000000.txt Download as CSV file: xf-curtisc72-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -0.7636 0.04425 0.04196 -0.0847 1.0000 0.0198
-14.000 -0.8081 0.03816 0.03570 -0.0882 1.0000 0.0198
-13.750 -0.8177 0.03571 0.03309 -0.0871 0.9994 0.0199
-13.500 -0.8066 0.02948 0.02635 -0.0939 0.9954 0.0204
-13.250 -0.7777 0.02805 0.02485 -0.0961 0.9940 0.0207
-13.000 -0.7485 0.02744 0.02421 -0.0973 0.9915 0.0210
-12.750 -0.7181 0.02686 0.02361 -0.0986 0.9891 0.0214
-12.500 -0.6872 0.02609 0.02279 -0.1001 0.9871 0.0218
-12.250 -0.6571 0.02475 0.02132 -0.1019 0.9852 0.0223
-12.000 -0.6263 0.02326 0.01964 -0.1039 0.9838 0.0228
-11.750 -0.5988 0.02202 0.01821 -0.1048 0.9801 0.0233
-11.500 -0.5698 0.02125 0.01729 -0.1056 0.9760 0.0238
-11.250 -0.5381 0.02109 0.01702 -0.1064 0.9728 0.0241
-11.000 -0.5174 0.01801 0.01366 -0.1069 0.9670 0.0249
-10.750 -0.4910 0.01718 0.01278 -0.1070 0.9609 0.0253
-10.500 -0.4629 0.01651 0.01204 -0.1072 0.9559 0.0257
-10.250 -0.4376 0.01590 0.01135 -0.1068 0.9480 0.0261
-10.000 -0.4103 0.01536 0.01073 -0.1067 0.9419 0.0266
-9.750 -0.3848 0.01486 0.01016 -0.1062 0.9338 0.0271
-9.250 -0.3324 0.01372 0.00882 -0.1054 0.9191 0.0280
-9.000 -0.3057 0.01326 0.00825 -0.1050 0.9121 0.0283
-8.750 -0.2791 0.01287 0.00779 -0.1047 0.9046 0.0286
-8.500 -0.2519 0.01261 0.00744 -0.1043 0.8974 0.0289
-8.250 -0.2274 0.01147 0.00621 -0.1038 0.8901 0.0296
-8.000 -0.2013 0.01091 0.00560 -0.1034 0.8825 0.0301
-7.750 -0.1745 0.01050 0.00515 -0.1031 0.8754 0.0306
-7.500 -0.1476 0.01015 0.00475 -0.1028 0.8676 0.0311
-7.250 -0.1204 0.00985 0.00440 -0.1025 0.8605 0.0316
-7.000 -0.0931 0.00955 0.00406 -0.1022 0.8523 0.0322
-6.750 -0.0657 0.00930 0.00375 -0.1019 0.8442 0.0328
-6.500 -0.0384 0.00907 0.00346 -0.1016 0.8343 0.0334
-6.250 -0.0108 0.00888 0.00322 -0.1014 0.8240 0.0340
-6.000 0.0166 0.00873 0.00300 -0.1011 0.8136 0.0345
-5.750 0.0439 0.00845 0.00265 -0.1008 0.8023 0.0352
-5.500 0.0712 0.00821 0.00236 -0.1005 0.7903 0.0364
-5.250 0.0988 0.00806 0.00215 -0.1003 0.7788 0.0377
-5.000 0.1265 0.00794 0.00198 -0.1000 0.7685 0.0390
-4.750 0.1545 0.00783 0.00183 -0.0999 0.7585 0.0406
-4.500 0.1823 0.00772 0.00168 -0.0997 0.7485 0.0439
-4.250 0.2100 0.00757 0.00157 -0.0995 0.7382 0.0565
-4.000 0.2377 0.00737 0.00147 -0.0994 0.7288 0.0895
-3.750 0.2652 0.00724 0.00139 -0.0993 0.7190 0.1179
-3.500 0.2927 0.00704 0.00133 -0.0992 0.7086 0.1681
-3.250 0.3201 0.00683 0.00127 -0.0992 0.6985 0.2283
-3.000 0.3471 0.00661 0.00124 -0.0990 0.6883 0.3035
-2.750 0.3747 0.00642 0.00123 -0.0990 0.6786 0.3720
-2.500 0.4021 0.00633 0.00125 -0.0989 0.6687 0.4276
-2.250 0.4297 0.00630 0.00127 -0.0988 0.6577 0.4678
-2.000 0.4576 0.00629 0.00129 -0.0987 0.6465 0.4936
-1.750 0.4854 0.00632 0.00131 -0.0986 0.6354 0.5124
-1.250 0.5406 0.00632 0.00138 -0.0984 0.6126 0.5649
-1.000 0.5680 0.00633 0.00142 -0.0983 0.6005 0.5935
-0.750 0.5952 0.00634 0.00147 -0.0981 0.5872 0.6221
-0.250 0.6481 0.00626 0.00160 -0.0976 0.5592 0.7298
0.000 0.6820 0.00583 0.00170 -0.0986 0.5433 1.0000
0.250 0.7086 0.00597 0.00176 -0.0984 0.5262 1.0000
0.500 0.7351 0.00613 0.00184 -0.0981 0.5078 1.0000
0.750 0.7614 0.00631 0.00192 -0.0979 0.4877 1.0000
1.000 0.7871 0.00653 0.00203 -0.0975 0.4652 1.0000
1.250 0.8128 0.00677 0.00214 -0.0972 0.4391 1.0000
1.500 0.8380 0.00705 0.00228 -0.0968 0.4109 1.0000
2.000 0.8890 0.00758 0.00258 -0.0962 0.3681 1.0000
2.250 0.9149 0.00780 0.00273 -0.0959 0.3535 1.0000
2.500 0.9413 0.00799 0.00287 -0.0958 0.3427 1.0000
2.750 0.9678 0.00817 0.00302 -0.0957 0.3333 1.0000
3.000 0.9937 0.00840 0.00319 -0.0955 0.3234 1.0000
3.250 1.0204 0.00855 0.00334 -0.0954 0.3158 1.0000
3.500 1.0463 0.00878 0.00352 -0.0952 0.3078 1.0000
3.750 1.0731 0.00892 0.00367 -0.0952 0.3015 1.0000
4.000 1.0989 0.00913 0.00386 -0.0950 0.2940 1.0000
4.250 1.1253 0.00930 0.00403 -0.0949 0.2875 1.0000
4.500 1.1510 0.00952 0.00423 -0.0948 0.2792 1.0000
4.750 1.1768 0.00973 0.00441 -0.0946 0.2683 1.0000
5.000 1.2018 0.00999 0.00463 -0.0944 0.2547 1.0000
5.250 1.2261 0.01031 0.00486 -0.0940 0.2371 1.0000
5.500 1.2492 0.01071 0.00515 -0.0935 0.2162 1.0000
5.750 1.2713 0.01118 0.00549 -0.0929 0.1902 1.0000
6.000 1.2927 0.01170 0.00589 -0.0921 0.1668 1.0000
6.250 1.3132 0.01228 0.00634 -0.0912 0.1451 1.0000
6.500 1.3342 0.01281 0.00677 -0.0904 0.1271 1.0000
6.750 1.3550 0.01333 0.00722 -0.0896 0.1125 1.0000
7.000 1.3760 0.01381 0.00765 -0.0888 0.1016 1.0000
7.250 1.3966 0.01431 0.00809 -0.0880 0.0921 1.0000
7.500 1.4173 0.01477 0.00853 -0.0871 0.0845 1.0000
7.750 1.4375 0.01524 0.00898 -0.0863 0.0766 1.0000
8.000 1.4561 0.01579 0.00949 -0.0852 0.0672 1.0000
8.250 1.4708 0.01649 0.01010 -0.0834 0.0530 1.0000
8.500 1.4798 0.01749 0.01096 -0.0808 0.0360 1.0000
8.750 1.4909 0.01837 0.01179 -0.0785 0.0277 1.0000
9.000 1.5030 0.01918 0.01261 -0.0765 0.0235 1.0000
9.250 1.5149 0.02002 0.01346 -0.0746 0.0210 1.0000
9.500 1.5278 0.02081 0.01429 -0.0729 0.0194 1.0000
9.750 1.5403 0.02164 0.01516 -0.0713 0.0181 1.0000
10.000 1.5500 0.02268 0.01624 -0.0694 0.0169 1.0000
10.250 1.5608 0.02368 0.01730 -0.0678 0.0161 1.0000
10.500 1.5724 0.02466 0.01834 -0.0664 0.0155 1.0000
10.750 1.5827 0.02576 0.01950 -0.0650 0.0149 1.0000
11.000 1.5913 0.02702 0.02081 -0.0635 0.0144 1.0000
11.250 1.5967 0.02858 0.02243 -0.0619 0.0138 1.0000
11.500 1.5982 0.03054 0.02448 -0.0601 0.0133 1.0000
11.750 1.6067 0.03198 0.02600 -0.0591 0.0130 1.0000
12.000 1.6134 0.03360 0.02771 -0.0581 0.0127 1.0000
12.250 1.6189 0.03540 0.02958 -0.0572 0.0124 1.0000
12.500 1.6234 0.03735 0.03161 -0.0563 0.0121 1.0000
12.750 1.6266 0.03949 0.03382 -0.0556 0.0118 1.0000
13.000 1.6280 0.04188 0.03629 -0.0549 0.0115 1.0000
13.250 1.6264 0.04469 0.03918 -0.0544 0.0112 1.0000
13.500 1.6211 0.04802 0.04262 -0.0540 0.0110 1.0000
13.750 1.6116 0.05201 0.04672 -0.0538 0.0108 1.0000
14.000 1.5990 0.05659 0.05143 -0.0540 0.0106 1.0000
14.250 1.5968 0.05998 0.05491 -0.0543 0.0105 1.0000
14.500 1.5928 0.06369 0.05873 -0.0548 0.0104 1.0000
14.750 1.5868 0.06776 0.06291 -0.0554 0.0103 1.0000
15.000 1.5797 0.07212 0.06738 -0.0563 0.0102 1.0000
15.250 1.5701 0.07688 0.07225 -0.0574 0.0101 1.0000
15.500 1.5603 0.08179 0.07727 -0.0586 0.0100 1.0000
15.750 1.5490 0.08704 0.08263 -0.0600 0.0099 1.0000
16.000 1.5374 0.09239 0.08809 -0.0615 0.0098 1.0000
16.250 1.5246 0.09799 0.09380 -0.0633 0.0097 1.0000
16.500 1.5121 0.10362 0.09954 -0.0651 0.0096 1.0000
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Polar data table (+)
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