cr001sm (cr001sm-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: cr001sm (cr001sm-il) Reynolds number: 50,000 Max Cl/Cd: 41.22 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-cr001sm-il-50000.txt Download as CSV file: xf-cr001sm-il-50000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3519 0.10144 0.09481 -0.0237 1.0000 0.1751
-7.250 -0.3645 0.10078 0.09430 -0.0228 1.0000 0.1805
-7.000 -0.3861 0.10137 0.09509 -0.0242 1.0000 0.1822
-6.750 -0.3661 0.09572 0.08943 -0.0199 1.0000 0.1933
-6.500 -0.3817 0.09519 0.08908 -0.0219 1.0000 0.1971
-6.250 -0.3701 0.09115 0.08506 -0.0182 1.0000 0.2078
-6.000 -0.3708 0.08848 0.08249 -0.0171 1.0000 0.2154
-5.750 -0.3811 0.08798 0.08209 -0.0208 1.0000 0.2253
-5.500 -0.3756 0.08462 0.07879 -0.0172 1.0000 0.2386
-5.250 -0.3737 0.08197 0.07622 -0.0157 1.0000 0.2527
-5.000 -0.3723 0.07963 0.07394 -0.0153 1.0000 0.2676
-4.750 -0.3701 0.07697 0.07136 -0.0145 1.0000 0.2839
-4.500 -0.3660 0.07399 0.06842 -0.0110 1.0000 0.3005
-4.250 -0.3619 0.07144 0.06593 -0.0085 1.0000 0.3198
-4.000 -0.3586 0.06902 0.06357 -0.0078 1.0000 0.3433
-3.750 -0.3546 0.06665 0.06125 -0.0061 1.0000 0.3710
-3.500 -0.3512 0.06419 0.05886 -0.0027 1.0000 0.4001
-3.250 -0.3488 0.06171 0.05647 0.0018 1.0000 0.4310
-3.000 -0.3484 0.05953 0.05437 0.0066 1.0000 0.4725
-2.500 -0.1129 0.03861 0.03072 -0.0633 1.0000 0.1553
-2.250 -0.0795 0.03552 0.02720 -0.0653 1.0000 0.1455
-2.000 -0.0438 0.03275 0.02371 -0.0671 1.0000 0.1348
-1.750 -0.0118 0.03051 0.02086 -0.0679 1.0000 0.1289
-1.500 0.0172 0.02891 0.01873 -0.0680 1.0000 0.1275
-1.250 0.0418 0.02779 0.01742 -0.0677 1.0000 0.1339
-1.000 0.0664 0.02683 0.01620 -0.0672 1.0000 0.1427
-0.750 0.0917 0.02607 0.01520 -0.0666 1.0000 0.1517
-0.500 0.1180 0.02542 0.01440 -0.0663 1.0000 0.1686
-0.250 0.1464 0.02467 0.01388 -0.0666 1.0000 0.2251
0.000 0.1703 0.02174 0.01305 -0.0648 1.0000 1.0000
0.250 0.1905 0.02235 0.01319 -0.0644 1.0000 1.0000
0.500 0.2100 0.02302 0.01353 -0.0641 1.0000 1.0000
0.750 0.2290 0.02375 0.01397 -0.0638 1.0000 1.0000
1.000 0.2473 0.02454 0.01454 -0.0636 1.0000 1.0000
1.250 0.2652 0.02539 0.01521 -0.0634 1.0000 1.0000
1.500 0.2827 0.02630 0.01597 -0.0632 1.0000 1.0000
1.750 0.3277 0.02770 0.01717 -0.0682 0.9870 1.0000
2.000 0.3766 0.02904 0.01837 -0.0737 0.9706 1.0000
2.250 0.4202 0.03017 0.01940 -0.0780 0.9530 1.0000
2.500 0.4646 0.03122 0.02041 -0.0822 0.9358 1.0000
2.750 0.5115 0.03220 0.02135 -0.0865 0.9189 1.0000
3.000 0.5497 0.03300 0.02217 -0.0892 0.9000 1.0000
3.250 0.5902 0.03370 0.02293 -0.0920 0.8810 1.0000
3.500 0.6390 0.03417 0.02348 -0.0957 0.8628 1.0000
3.750 0.6731 0.03468 0.02407 -0.0969 0.8416 1.0000
4.000 0.7211 0.03474 0.02432 -0.0997 0.8222 1.0000
4.250 0.7605 0.03482 0.02455 -0.1009 0.8010 1.0000
4.500 0.8113 0.03425 0.02419 -0.1031 0.7806 1.0000
4.750 0.8588 0.03352 0.02376 -0.1044 0.7589 1.0000
5.000 0.9137 0.03210 0.02262 -0.1058 0.7376 1.0000
5.250 0.9554 0.03113 0.02188 -0.1054 0.7123 1.0000
5.500 0.9998 0.02986 0.02091 -0.1049 0.6848 1.0000
5.750 1.0434 0.02854 0.01978 -0.1040 0.6533 1.0000
6.000 1.0760 0.02794 0.01929 -0.1021 0.6165 1.0000
6.250 1.1066 0.02755 0.01892 -0.1000 0.5757 1.0000
6.500 1.1317 0.02762 0.01901 -0.0974 0.5316 1.0000
6.750 1.1538 0.02799 0.01928 -0.0947 0.4861 1.0000
7.000 1.1741 0.02860 0.01972 -0.0920 0.4408 1.0000
7.250 1.1925 0.02942 0.02031 -0.0893 0.3958 1.0000
7.500 1.2068 0.03053 0.02130 -0.0863 0.3513 1.0000
7.750 1.2197 0.03187 0.02252 -0.0833 0.3067 1.0000
8.000 1.2314 0.03353 0.02396 -0.0802 0.2621 1.0000
8.250 1.2428 0.03560 0.02581 -0.0774 0.2197 1.0000
8.500 1.2555 0.03803 0.02799 -0.0748 0.1828 1.0000
8.750 1.2684 0.04059 0.03053 -0.0724 0.1542 1.0000
9.000 1.2865 0.04355 0.03346 -0.0708 0.1336 1.0000
9.250 1.3034 0.04664 0.03654 -0.0693 0.1180 1.0000
9.500 1.3143 0.05032 0.04086 -0.0667 0.1103 1.0000
9.750 1.3270 0.05422 0.04505 -0.0649 0.1034 1.0000
10.000 1.3272 0.05787 0.04928 -0.0618 0.0986 1.0000
10.250 1.3453 0.06215 0.05343 -0.0612 0.0925 1.0000
10.500 1.3384 0.06655 0.05840 -0.0579 0.0920 1.0000
10.750 1.3280 0.07110 0.06341 -0.0548 0.0918 1.0000
11.000 1.3148 0.07570 0.06838 -0.0520 0.0918 1.0000
11.250 1.2988 0.08022 0.07317 -0.0493 0.0921 1.0000
11.500 1.2815 0.08480 0.07796 -0.0470 0.0924 1.0000
11.750 1.0465 0.09266 0.08682 -0.0426 0.1146 1.0000
12.000 1.0151 0.10095 0.09518 -0.0459 0.1169 1.0000
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Polar data table (+)
Polar graphs
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