cr001sm (cr001sm-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: cr001sm (cr001sm-il) Reynolds number: 100,000 Max Cl/Cd: 64.26 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-cr001sm-il-100000-n5.txt Download as CSV file: xf-cr001sm-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: cr001sm
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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3560 0.10379 0.09886 -0.0321 1.0000 0.0415
-8.000 -0.3631 0.10218 0.09736 -0.0322 1.0000 0.0417
-7.750 -0.3711 0.10057 0.09584 -0.0317 1.0000 0.0419
-7.500 -0.3750 0.09835 0.09371 -0.0326 1.0000 0.0420
-7.250 -0.3759 0.09575 0.09117 -0.0340 1.0000 0.0421
-7.000 -0.3677 0.09052 0.08595 -0.0260 1.0000 0.0447
-6.750 -0.3681 0.08823 0.08372 -0.0246 1.0000 0.0464
-6.500 -0.3703 0.08595 0.08150 -0.0240 1.0000 0.0477
-6.250 -0.3719 0.08353 0.07915 -0.0241 1.0000 0.0486
-6.000 -0.3721 0.08091 0.07658 -0.0248 1.0000 0.0500
-5.750 -0.3698 0.07800 0.07370 -0.0267 1.0000 0.0516
-5.500 -0.3224 0.07150 0.06694 -0.0478 0.9950 0.0551
-5.000 -0.2779 0.06145 0.05689 -0.0541 0.9863 0.0571
-4.750 -0.2498 0.05725 0.05261 -0.0585 0.9810 0.0585
-4.500 -0.1944 0.04626 0.04098 -0.0707 0.9764 0.0296
-4.250 -0.1580 0.04149 0.03595 -0.0762 0.9728 0.0285
-4.000 -0.1239 0.03701 0.03109 -0.0803 0.9671 0.0277
-3.750 -0.0850 0.03278 0.02630 -0.0844 0.9627 0.0276
-3.500 -0.0434 0.02961 0.02241 -0.0879 0.9595 0.0298
-3.250 -0.0107 0.02737 0.01959 -0.0892 0.9533 0.0304
-3.000 0.0249 0.02480 0.01655 -0.0911 0.9490 0.0307
-2.750 0.0623 0.02257 0.01394 -0.0932 0.9458 0.0316
-2.500 0.0920 0.02119 0.01233 -0.0936 0.9389 0.0330
-2.250 0.1276 0.02025 0.01123 -0.0951 0.9340 0.0381
-2.000 0.1610 0.01923 0.01004 -0.0960 0.9284 0.0406
-1.750 0.1934 0.01825 0.00898 -0.0967 0.9221 0.0432
-1.500 0.2312 0.01747 0.00816 -0.0986 0.9181 0.0512
-1.250 0.2603 0.01690 0.00752 -0.0987 0.9094 0.0595
-1.000 0.2987 0.01613 0.00682 -0.1006 0.9049 0.0914
-0.750 0.3286 0.01493 0.00670 -0.1016 0.8971 0.3950
-0.500 0.3655 0.01333 0.00648 -0.1025 0.8925 1.0000
-0.250 0.3974 0.01332 0.00624 -0.1031 0.8837 1.0000
0.000 0.4339 0.01325 0.00596 -0.1045 0.8768 1.0000
0.250 0.4638 0.01325 0.00580 -0.1047 0.8662 1.0000
0.500 0.4958 0.01323 0.00564 -0.1053 0.8564 1.0000
0.750 0.5312 0.01315 0.00544 -0.1064 0.8480 1.0000
1.000 0.5607 0.01317 0.00537 -0.1065 0.8359 1.0000
1.250 0.5909 0.01317 0.00530 -0.1067 0.8237 1.0000
1.500 0.6213 0.01318 0.00524 -0.1069 0.8109 1.0000
1.750 0.6516 0.01319 0.00519 -0.1070 0.7972 1.0000
2.000 0.6817 0.01320 0.00516 -0.1071 0.7820 1.0000
2.250 0.7118 0.01322 0.00512 -0.1071 0.7656 1.0000
2.500 0.7404 0.01327 0.00512 -0.1069 0.7469 1.0000
2.750 0.7681 0.01335 0.00515 -0.1064 0.7268 1.0000
3.000 0.7963 0.01345 0.00522 -0.1061 0.7068 1.0000
3.250 0.8223 0.01361 0.00534 -0.1054 0.6850 1.0000
3.500 0.8489 0.01378 0.00545 -0.1048 0.6634 1.0000
3.750 0.8744 0.01399 0.00562 -0.1041 0.6403 1.0000
4.000 0.8995 0.01422 0.00586 -0.1033 0.6167 1.0000
4.250 0.9242 0.01449 0.00608 -0.1024 0.5925 1.0000
4.500 0.9482 0.01479 0.00634 -0.1014 0.5668 1.0000
4.750 0.9716 0.01512 0.00664 -0.1004 0.5400 1.0000
5.000 0.9945 0.01549 0.00696 -0.0993 0.5116 1.0000
5.250 1.0166 0.01590 0.00736 -0.0980 0.4817 1.0000
5.500 1.0381 0.01635 0.00777 -0.0967 0.4498 1.0000
5.750 1.0589 0.01686 0.00821 -0.0953 0.4154 1.0000
6.000 1.0787 0.01744 0.00870 -0.0938 0.3795 1.0000
6.250 1.0979 0.01808 0.00928 -0.0923 0.3421 1.0000
6.500 1.1164 0.01879 0.00989 -0.0907 0.3057 1.0000
6.750 1.1344 0.01957 0.01056 -0.0891 0.2714 1.0000
7.000 1.1520 0.02040 0.01130 -0.0875 0.2394 1.0000
7.250 1.1694 0.02126 0.01209 -0.0860 0.2089 1.0000
7.500 1.1864 0.02217 0.01293 -0.0844 0.1794 1.0000
7.750 1.2028 0.02312 0.01387 -0.0828 0.1505 1.0000
8.000 1.2182 0.02418 0.01484 -0.0810 0.1213 1.0000
8.250 1.2323 0.02537 0.01593 -0.0792 0.0943 1.0000
8.500 1.2453 0.02668 0.01717 -0.0772 0.0723 1.0000
8.750 1.2562 0.02816 0.01859 -0.0749 0.0573 1.0000
9.000 1.2666 0.02963 0.02014 -0.0725 0.0478 1.0000
9.250 1.2747 0.03116 0.02173 -0.0698 0.0410 1.0000
9.500 1.2818 0.03265 0.02338 -0.0670 0.0361 1.0000
9.750 1.2848 0.03452 0.02533 -0.0638 0.0335 1.0000
10.000 1.2912 0.03626 0.02729 -0.0611 0.0312 1.0000
10.250 1.2972 0.03805 0.02925 -0.0586 0.0288 1.0000
10.500 1.3016 0.03988 0.03119 -0.0563 0.0266 1.0000
10.750 1.3029 0.04230 0.03367 -0.0539 0.0248 1.0000
11.000 1.3097 0.04444 0.03609 -0.0519 0.0235 1.0000
11.250 1.3152 0.04692 0.03883 -0.0500 0.0225 1.0000
11.500 1.3193 0.04960 0.04176 -0.0482 0.0216 1.0000
11.750 1.3210 0.05244 0.04485 -0.0465 0.0207 1.0000
12.000 1.3202 0.05532 0.04796 -0.0450 0.0199 1.0000
12.250 1.3171 0.05830 0.05117 -0.0439 0.0191 1.0000
12.500 1.3123 0.06157 0.05460 -0.0431 0.0184 1.0000
12.750 1.3050 0.06548 0.05868 -0.0426 0.0178 1.0000
13.000 1.2941 0.07013 0.06354 -0.0426 0.0174 1.0000
13.250 1.2824 0.07481 0.06853 -0.0432 0.0172 1.0000
13.500 1.2690 0.08004 0.07403 -0.0445 0.0170 1.0000
13.750 1.2536 0.08589 0.08016 -0.0466 0.0169 1.0000
14.000 1.2369 0.09236 0.08687 -0.0495 0.0169 1.0000
14.250 1.2195 0.09943 0.09416 -0.0532 0.0169 1.0000
14.500 1.2015 0.10711 0.10204 -0.0576 0.0170 1.0000
14.750 1.1832 0.11551 0.11063 -0.0628 0.0171 1.0000
15.000 1.1650 0.12450 0.11977 -0.0686 0.0172 1.0000
15.250 1.1476 0.13391 0.12929 -0.0746 0.0174 1.0000
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Polar data table (+)
Polar graphs
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