cr001sm (cr001sm-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: cr001sm (cr001sm-il) Reynolds number: 100,000 Max Cl/Cd: 64.83 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-cr001sm-il-100000.txt Download as CSV file: xf-cr001sm-il-100000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3535 0.09932 0.09453 -0.0291 1.0000 0.0672
-7.500 -0.3685 0.09876 0.09410 -0.0285 1.0000 0.0680
-7.250 -0.3779 0.09750 0.09297 -0.0297 1.0000 0.0684
-7.000 -0.3826 0.09587 0.09142 -0.0339 1.0000 0.0687
-6.750 -0.3718 0.08997 0.08552 -0.0244 1.0000 0.0721
-6.500 -0.3715 0.08762 0.08323 -0.0229 1.0000 0.0748
-6.250 -0.3733 0.08537 0.08104 -0.0227 1.0000 0.0770
-6.000 -0.3746 0.08303 0.07876 -0.0248 1.0000 0.0802
-5.750 -0.3615 0.08048 0.07606 -0.0415 1.0000 0.0828
-5.500 -0.3667 0.07632 0.07210 -0.0324 1.0000 0.0842
-5.250 -0.3649 0.07386 0.06970 -0.0281 1.0000 0.0868
-5.000 -0.3576 0.07117 0.06702 -0.0286 1.0000 0.0907
-4.750 -0.3323 0.06627 0.06195 -0.0404 1.0000 0.0979
-4.500 -0.3304 0.06387 0.05965 -0.0359 1.0000 0.1004
-4.250 -0.2996 0.05967 0.05519 -0.0453 1.0000 0.1119
-4.000 -0.2961 0.05722 0.05288 -0.0413 1.0000 0.1147
-3.750 -0.2702 0.05361 0.04907 -0.0463 1.0000 0.1272
-3.500 -0.2470 0.05067 0.04599 -0.0493 1.0000 0.1408
-3.250 -0.2356 0.04853 0.04393 -0.0473 1.0000 0.1479
-3.000 -0.2078 0.04559 0.04080 -0.0512 1.0000 0.1702
-2.750 -0.1903 0.04349 0.03872 -0.0509 1.0000 0.1871
-2.500 -0.1718 0.04171 0.03694 -0.0509 1.0000 0.2161
-2.000 -0.0313 0.02842 0.02089 -0.0677 0.9965 0.0814
-1.750 0.0137 0.02558 0.01749 -0.0706 0.9918 0.0734
-1.500 0.0587 0.02408 0.01555 -0.0736 0.9862 0.0742
-1.250 0.0999 0.02301 0.01422 -0.0759 0.9790 0.0785
-1.000 0.1447 0.02211 0.01308 -0.0787 0.9732 0.0822
-0.750 0.1821 0.02125 0.01229 -0.0806 0.9647 0.0948
-0.500 0.2274 0.02051 0.01166 -0.0839 0.9588 0.1207
-0.250 0.2664 0.01765 0.01127 -0.0856 0.9525 1.0000
0.000 0.3136 0.01795 0.01117 -0.0895 0.9448 1.0000
0.250 0.3520 0.01813 0.01112 -0.0917 0.9338 1.0000
0.500 0.3900 0.01830 0.01110 -0.0938 0.9229 1.0000
0.750 0.4307 0.01841 0.01106 -0.0963 0.9130 1.0000
1.000 0.4770 0.01840 0.01092 -0.0997 0.9048 1.0000
1.250 0.5136 0.01841 0.01086 -0.1012 0.8931 1.0000
1.500 0.5522 0.01835 0.01075 -0.1031 0.8820 1.0000
1.750 0.6057 0.01794 0.01032 -0.1073 0.8761 1.0000
2.000 0.6432 0.01773 0.01010 -0.1086 0.8638 1.0000
2.250 0.6811 0.01744 0.00983 -0.1098 0.8514 1.0000
2.500 0.7194 0.01707 0.00947 -0.1109 0.8386 1.0000
2.750 0.7568 0.01668 0.00911 -0.1117 0.8251 1.0000
3.000 0.7926 0.01631 0.00880 -0.1122 0.8104 1.0000
3.250 0.8271 0.01599 0.00851 -0.1124 0.7948 1.0000
3.500 0.8608 0.01571 0.00824 -0.1125 0.7782 1.0000
3.750 0.8875 0.01568 0.00823 -0.1115 0.7575 1.0000
4.000 0.9175 0.01556 0.00816 -0.1109 0.7374 1.0000
4.250 0.9437 0.01559 0.00822 -0.1099 0.7146 1.0000
4.500 0.9711 0.01562 0.00822 -0.1089 0.6912 1.0000
4.750 0.9966 0.01573 0.00832 -0.1077 0.6656 1.0000
5.000 1.0206 0.01591 0.00852 -0.1063 0.6376 1.0000
5.250 1.0438 0.01614 0.00872 -0.1048 0.6076 1.0000
5.500 1.0651 0.01643 0.00901 -0.1030 0.5741 1.0000
5.750 1.0862 0.01679 0.00928 -0.1011 0.5385 1.0000
6.000 1.1054 0.01723 0.00965 -0.0991 0.4988 1.0000
6.250 1.1235 0.01777 0.01011 -0.0969 0.4564 1.0000
6.500 1.1405 0.01842 0.01061 -0.0946 0.4126 1.0000
6.750 1.1565 0.01920 0.01121 -0.0923 0.3690 1.0000
7.000 1.1719 0.02007 0.01192 -0.0901 0.3270 1.0000
7.250 1.1867 0.02103 0.01273 -0.0878 0.2871 1.0000
7.500 1.2006 0.02208 0.01364 -0.0856 0.2489 1.0000
7.750 1.2129 0.02328 0.01468 -0.0832 0.2123 1.0000
8.000 1.2236 0.02460 0.01586 -0.0806 0.1737 1.0000
8.250 1.2326 0.02618 0.01726 -0.0778 0.1353 1.0000
8.500 1.2401 0.02808 0.01890 -0.0749 0.1058 1.0000
8.750 1.2515 0.03007 0.02088 -0.0723 0.0854 1.0000
9.000 1.2643 0.03204 0.02281 -0.0702 0.0721 1.0000
9.250 1.2826 0.03452 0.02533 -0.0688 0.0635 1.0000
9.500 1.3048 0.03718 0.02801 -0.0681 0.0572 1.0000
9.750 1.3245 0.04005 0.03121 -0.0668 0.0523 1.0000
10.000 1.3401 0.04245 0.03386 -0.0652 0.0483 1.0000
10.250 1.3589 0.04599 0.03756 -0.0643 0.0459 1.0000
10.500 1.3727 0.05176 0.04370 -0.0633 0.0446 1.0000
10.750 1.3719 0.05485 0.04726 -0.0599 0.0440 1.0000
11.000 1.3655 0.05777 0.05066 -0.0561 0.0433 1.0000
11.250 1.3544 0.06086 0.05414 -0.0521 0.0428 1.0000
11.500 1.3393 0.06403 0.05765 -0.0481 0.0424 1.0000
11.750 1.3216 0.06753 0.06146 -0.0449 0.0421 1.0000
12.000 1.3027 0.07151 0.06572 -0.0427 0.0422 1.0000
12.250 1.2820 0.07596 0.07043 -0.0414 0.0423 1.0000
12.500 1.2603 0.08095 0.07565 -0.0412 0.0425 1.0000
12.750 1.2381 0.08656 0.08146 -0.0422 0.0429 1.0000
13.000 1.2156 0.09279 0.08788 -0.0443 0.0433 1.0000
13.250 1.1942 0.09967 0.09490 -0.0473 0.0438 1.0000
13.500 1.1748 0.10713 0.10246 -0.0508 0.0443 1.0000
13.750 1.1568 0.11450 0.10999 -0.0551 0.0449 1.0000
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Polar data table (+)
Polar graphs
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