Curtis C-72 (curtisc72-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: Curtis C-72 (curtisc72-il) Reynolds number: 200,000 Max Cl/Cd: 73.28 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-curtisc72-il-200000-n5.txt Download as CSV file: xf-curtisc72-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.3938 0.08903 0.08526 -0.0451 1.0000 0.0320
-11.500 -0.4015 0.08475 0.08104 -0.0465 1.0000 0.0324
-11.250 -0.4153 0.08019 0.07656 -0.0476 1.0000 0.0326
-11.000 -0.4383 0.07584 0.07231 -0.0475 1.0000 0.0326
-10.750 -0.5041 0.04281 0.03858 -0.0857 0.9785 0.0322
-10.500 -0.4894 0.03599 0.03108 -0.0918 0.9715 0.0331
-10.250 -0.4691 0.03195 0.02645 -0.0944 0.9645 0.0342
-10.000 -0.4409 0.02885 0.02278 -0.0970 0.9609 0.0350
-9.750 -0.4171 0.02685 0.02035 -0.0975 0.9539 0.0354
-9.500 -0.3885 0.02480 0.01803 -0.0987 0.9495 0.0359
-9.250 -0.3576 0.02342 0.01654 -0.1000 0.9460 0.0368
-9.000 -0.3315 0.02248 0.01550 -0.1001 0.9390 0.0376
-8.750 -0.3007 0.02143 0.01428 -0.1010 0.9344 0.0384
-8.500 -0.2701 0.02036 0.01304 -0.1017 0.9300 0.0391
-8.250 -0.2429 0.01945 0.01198 -0.1016 0.9229 0.0397
-8.000 -0.2122 0.01856 0.01095 -0.1022 0.9180 0.0404
-7.750 -0.1833 0.01779 0.01006 -0.1024 0.9120 0.0411
-7.500 -0.1552 0.01712 0.00929 -0.1024 0.9052 0.0419
-7.250 -0.1242 0.01654 0.00859 -0.1029 0.9001 0.0428
-7.000 -0.0986 0.01586 0.00792 -0.1025 0.8920 0.0441
-6.750 -0.0696 0.01532 0.00735 -0.1026 0.8857 0.0452
-6.500 -0.0424 0.01488 0.00687 -0.1024 0.8780 0.0463
-6.250 -0.0144 0.01446 0.00640 -0.1022 0.8707 0.0477
-6.000 0.0133 0.01410 0.00597 -0.1021 0.8633 0.0492
-5.750 0.0409 0.01377 0.00558 -0.1018 0.8553 0.0510
-5.500 0.0687 0.01343 0.00522 -0.1017 0.8477 0.0538
-5.250 0.0962 0.01316 0.00494 -0.1015 0.8394 0.0587
-5.000 0.1239 0.01288 0.00467 -0.1013 0.8313 0.0673
-4.750 0.1515 0.01261 0.00439 -0.1010 0.8228 0.0821
-4.500 0.1787 0.01234 0.00415 -0.1008 0.8131 0.1014
-4.250 0.2062 0.01206 0.00392 -0.1006 0.8027 0.1293
-4.000 0.2329 0.01176 0.00372 -0.1002 0.7894 0.1717
-3.750 0.2591 0.01141 0.00357 -0.0999 0.7756 0.2367
-3.500 0.2853 0.01105 0.00348 -0.0996 0.7634 0.3270
-3.250 0.3117 0.01081 0.00349 -0.0992 0.7533 0.4155
-3.000 0.3386 0.01071 0.00348 -0.0989 0.7429 0.4711
-2.750 0.3655 0.01065 0.00346 -0.0985 0.7325 0.5069
-2.500 0.3926 0.01060 0.00342 -0.0981 0.7226 0.5362
-2.250 0.4192 0.01054 0.00341 -0.0977 0.7116 0.5693
-2.000 0.4455 0.01046 0.00342 -0.0972 0.7006 0.6062
-1.750 0.4716 0.01038 0.00341 -0.0966 0.6901 0.6456
-1.500 0.4969 0.01027 0.00342 -0.0959 0.6790 0.6917
-1.250 0.5210 0.01008 0.00344 -0.0948 0.6674 0.7575
-1.000 0.5611 0.00978 0.00341 -0.0966 0.6547 0.9775
-0.750 0.5896 0.00989 0.00340 -0.0968 0.6425 1.0000
-0.500 0.6162 0.01001 0.00343 -0.0965 0.6299 1.0000
-0.250 0.6426 0.01015 0.00347 -0.0962 0.6163 1.0000
0.000 0.6688 0.01029 0.00352 -0.0958 0.6019 1.0000
0.250 0.6948 0.01045 0.00359 -0.0954 0.5872 1.0000
0.500 0.7208 0.01062 0.00368 -0.0951 0.5725 1.0000
0.750 0.7465 0.01080 0.00377 -0.0947 0.5569 1.0000
1.000 0.7720 0.01100 0.00388 -0.0942 0.5399 1.0000
1.250 0.7971 0.01121 0.00401 -0.0937 0.5223 1.0000
1.500 0.8222 0.01145 0.00416 -0.0932 0.5049 1.0000
1.750 0.8469 0.01170 0.00433 -0.0927 0.4870 1.0000
2.000 0.8713 0.01198 0.00452 -0.0922 0.4690 1.0000
2.250 0.8957 0.01226 0.00472 -0.0916 0.4512 1.0000
2.500 0.9199 0.01256 0.00496 -0.0911 0.4340 1.0000
2.750 0.9438 0.01288 0.00520 -0.0905 0.4174 1.0000
3.000 0.9676 0.01322 0.00547 -0.0899 0.4017 1.0000
3.250 0.9910 0.01358 0.00575 -0.0893 0.3857 1.0000
3.500 1.0139 0.01396 0.00606 -0.0886 0.3687 1.0000
3.750 1.0368 0.01434 0.00638 -0.0880 0.3532 1.0000
4.000 1.0600 0.01472 0.00671 -0.0874 0.3415 1.0000
4.250 1.0837 0.01506 0.00706 -0.0869 0.3316 1.0000
4.500 1.1073 0.01541 0.00742 -0.0864 0.3232 1.0000
4.750 1.1306 0.01578 0.00779 -0.0858 0.3145 1.0000
5.000 1.1539 0.01613 0.00819 -0.0853 0.3058 1.0000
5.250 1.1761 0.01654 0.00859 -0.0846 0.2963 1.0000
5.500 1.1990 0.01689 0.00900 -0.0840 0.2861 1.0000
5.750 1.2210 0.01730 0.00943 -0.0833 0.2765 1.0000
6.000 1.2424 0.01771 0.00989 -0.0826 0.2661 1.0000
6.250 1.2640 0.01811 0.01035 -0.0818 0.2550 1.0000
6.500 1.2842 0.01857 0.01083 -0.0809 0.2422 1.0000
6.750 1.3032 0.01908 0.01135 -0.0798 0.2271 1.0000
7.000 1.3194 0.01971 0.01194 -0.0784 0.2066 1.0000
7.250 1.3320 0.02049 0.01260 -0.0764 0.1813 1.0000
7.500 1.3420 0.02144 0.01341 -0.0741 0.1580 1.0000
7.750 1.3527 0.02240 0.01429 -0.0721 0.1398 1.0000
8.000 1.3642 0.02333 0.01519 -0.0702 0.1267 1.0000
8.250 1.3757 0.02429 0.01616 -0.0684 0.1165 1.0000
8.500 1.3857 0.02535 0.01721 -0.0666 0.1072 1.0000
8.750 1.3973 0.02634 0.01825 -0.0650 0.0985 1.0000
9.000 1.4071 0.02747 0.01941 -0.0634 0.0909 1.0000
9.250 1.4157 0.02872 0.02068 -0.0617 0.0830 1.0000
9.500 1.4252 0.02995 0.02198 -0.0603 0.0750 1.0000
9.750 1.4326 0.03138 0.02345 -0.0588 0.0665 1.0000
10.000 1.4386 0.03297 0.02505 -0.0574 0.0568 1.0000
10.250 1.4422 0.03482 0.02690 -0.0559 0.0474 1.0000
10.500 1.4436 0.03693 0.02902 -0.0545 0.0402 1.0000
11.000 1.4441 0.04164 0.03383 -0.0522 0.0317 1.0000
11.250 1.4418 0.04439 0.03665 -0.0512 0.0292 1.0000
11.500 1.4416 0.04703 0.03943 -0.0506 0.0273 1.0000
11.750 1.4394 0.04997 0.04249 -0.0500 0.0258 1.0000
12.000 1.4349 0.05327 0.04589 -0.0497 0.0246 1.0000
12.250 1.4288 0.05691 0.04964 -0.0497 0.0237 1.0000
12.500 1.4251 0.06040 0.05327 -0.0498 0.0228 1.0000
12.750 1.4201 0.06418 0.05720 -0.0502 0.0220 1.0000
13.000 1.4139 0.06825 0.06141 -0.0508 0.0213 1.0000
13.250 1.4064 0.07263 0.06592 -0.0516 0.0207 1.0000
13.500 1.3974 0.07734 0.07076 -0.0527 0.0201 1.0000
13.750 1.3868 0.08245 0.07598 -0.0540 0.0197 1.0000
14.000 1.3757 0.08774 0.08138 -0.0555 0.0193 1.0000
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Polar data table (+)
Polar graphs
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