cr001sm (cr001sm-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: cr001sm (cr001sm-il) Reynolds number: 50,000 Max Cl/Cd: 44.23 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-cr001sm-il-50000-n5.txt Download as CSV file: xf-cr001sm-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3565 0.11054 0.10353 -0.0295 1.0000 0.0949
-8.250 -0.3672 0.10984 0.10298 -0.0306 1.0000 0.0963
-8.000 -0.3802 0.10911 0.10241 -0.0310 1.0000 0.0967
-7.750 -0.3579 0.10266 0.09590 -0.0288 1.0000 0.0994
-7.500 -0.3542 0.09980 0.09310 -0.0276 1.0000 0.1024
-7.250 -0.3575 0.09776 0.09116 -0.0266 1.0000 0.1051
-7.000 -0.3656 0.09620 0.08974 -0.0265 1.0000 0.1085
-6.750 -0.3781 0.09542 0.08911 -0.0318 1.0000 0.1108
-6.500 -0.3718 0.09124 0.08501 -0.0285 1.0000 0.1124
-6.250 -0.3668 0.08815 0.08197 -0.0263 1.0000 0.1150
-6.000 -0.3647 0.08553 0.07940 -0.0260 1.0000 0.1183
-5.750 -0.3642 0.08345 0.07736 -0.0352 1.0000 0.1253
-5.250 -0.3536 0.07743 0.07143 -0.0320 1.0000 0.1382
-4.750 -0.3061 0.06426 0.05784 -0.0461 1.0000 0.0680
-4.500 -0.2958 0.06106 0.05467 -0.0455 1.0000 0.0656
-4.250 -0.2563 0.05396 0.04696 -0.0553 1.0000 0.0554
-4.000 -0.2412 0.05084 0.04383 -0.0552 1.0000 0.0538
-3.750 -0.2188 0.04722 0.04002 -0.0571 1.0000 0.0523
-3.500 -0.1917 0.04347 0.03592 -0.0598 1.0000 0.0508
-3.250 -0.1620 0.03988 0.03189 -0.0624 1.0000 0.0496
-3.000 -0.1315 0.03667 0.02817 -0.0646 1.0000 0.0490
-2.750 -0.1017 0.03410 0.02507 -0.0660 1.0000 0.0499
-2.500 -0.0632 0.03182 0.02211 -0.0686 0.9966 0.0533
-2.250 -0.0227 0.02983 0.01944 -0.0711 0.9915 0.0550
-2.000 0.0157 0.02796 0.01721 -0.0733 0.9863 0.0568
-1.750 0.0516 0.02669 0.01571 -0.0750 0.9799 0.0607
-1.500 0.0899 0.02586 0.01452 -0.0768 0.9736 0.0691
-1.250 0.1259 0.02493 0.01344 -0.0785 0.9665 0.0761
-1.000 0.1663 0.02422 0.01253 -0.0809 0.9600 0.0906
-0.750 0.2033 0.02342 0.01184 -0.0829 0.9519 0.1306
-0.500 0.2365 0.02099 0.01179 -0.0840 0.9474 0.6862
-0.250 0.2717 0.02067 0.01133 -0.0852 0.9358 1.0000
0.000 0.3075 0.02092 0.01117 -0.0869 0.9257 1.0000
0.250 0.3467 0.02115 0.01107 -0.0892 0.9169 1.0000
0.500 0.3808 0.02135 0.01104 -0.0906 0.9060 1.0000
0.750 0.4140 0.02156 0.01103 -0.0917 0.8947 1.0000
1.000 0.4485 0.02173 0.01105 -0.0930 0.8838 1.0000
1.250 0.4862 0.02184 0.01104 -0.0948 0.8741 1.0000
1.500 0.5218 0.02194 0.01106 -0.0961 0.8633 1.0000
2.000 0.5872 0.02217 0.01119 -0.0976 0.8388 1.0000
2.250 0.6200 0.02224 0.01124 -0.0983 0.8264 1.0000
2.500 0.6529 0.02228 0.01131 -0.0988 0.8136 1.0000
2.750 0.6854 0.02230 0.01135 -0.0992 0.8002 1.0000
3.000 0.7174 0.02229 0.01138 -0.0995 0.7858 1.0000
3.250 0.7490 0.02226 0.01144 -0.0995 0.7702 1.0000
3.500 0.7807 0.02218 0.01142 -0.0995 0.7538 1.0000
3.750 0.8132 0.02206 0.01136 -0.0994 0.7366 1.0000
4.000 0.8409 0.02210 0.01147 -0.0987 0.7165 1.0000
4.250 0.8703 0.02208 0.01158 -0.0981 0.6961 1.0000
4.500 0.8978 0.02215 0.01172 -0.0973 0.6740 1.0000
4.750 0.9264 0.02219 0.01182 -0.0966 0.6512 1.0000
5.000 0.9514 0.02238 0.01210 -0.0954 0.6257 1.0000
5.250 0.9764 0.02261 0.01238 -0.0942 0.5989 1.0000
5.500 1.0006 0.02288 0.01278 -0.0929 0.5706 1.0000
5.750 1.0238 0.02323 0.01316 -0.0915 0.5403 1.0000
6.000 1.0460 0.02365 0.01359 -0.0899 0.5086 1.0000
6.250 1.0659 0.02418 0.01417 -0.0881 0.4742 1.0000
6.500 1.0853 0.02479 0.01481 -0.0863 0.4390 1.0000
6.750 1.1029 0.02552 0.01554 -0.0843 0.4021 1.0000
7.000 1.1196 0.02635 0.01632 -0.0823 0.3658 1.0000
7.250 1.1349 0.02730 0.01723 -0.0802 0.3295 1.0000
7.500 1.1491 0.02838 0.01824 -0.0781 0.2950 1.0000
7.750 1.1623 0.02956 0.01938 -0.0759 0.2615 1.0000
8.000 1.1739 0.03088 0.02069 -0.0737 0.2299 1.0000
8.250 1.1839 0.03231 0.02205 -0.0714 0.1999 1.0000
8.500 1.1931 0.03386 0.02357 -0.0691 0.1707 1.0000
8.750 1.2003 0.03556 0.02522 -0.0667 0.1443 1.0000
9.000 1.2063 0.03735 0.02702 -0.0642 0.1207 1.0000
9.250 1.2119 0.03936 0.02900 -0.0616 0.1026 1.0000
9.500 1.2174 0.04144 0.03113 -0.0593 0.0872 1.0000
9.750 1.2237 0.04370 0.03343 -0.0570 0.0768 1.0000
10.000 1.2286 0.04595 0.03572 -0.0550 0.0684 1.0000
10.250 1.2371 0.04833 0.03843 -0.0531 0.0606 1.0000
10.500 1.2449 0.05091 0.04100 -0.0514 0.0561 1.0000
10.750 1.2558 0.05377 0.04428 -0.0498 0.0513 1.0000
11.000 1.2590 0.05645 0.04717 -0.0481 0.0475 1.0000
11.250 1.2628 0.05937 0.05004 -0.0469 0.0446 1.0000
11.500 1.2648 0.06301 0.05418 -0.0454 0.0429 1.0000
11.750 1.2619 0.06704 0.05864 -0.0441 0.0417 1.0000
12.000 1.2543 0.07136 0.06332 -0.0432 0.0410 1.0000
12.250 1.2426 0.07610 0.06840 -0.0430 0.0404 1.0000
12.500 1.2274 0.08134 0.07394 -0.0435 0.0401 1.0000
12.750 1.2095 0.08721 0.08009 -0.0451 0.0401 1.0000
13.000 1.1891 0.09389 0.08702 -0.0478 0.0402 1.0000
13.250 1.1668 0.10149 0.09483 -0.0517 0.0405 1.0000
13.500 1.1434 0.11011 0.10363 -0.0569 0.0410 1.0000
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Polar data table (+)
Polar graphs
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