S2046 (s2046-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: S2046 (s2046-il) Reynolds number: 1,000,000 Max Cl/Cd: 93.42 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s2046-il-1000000-n5.txt Download as CSV file: xf-s2046-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S2046
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.7847 0.06385 0.06178 -0.0469 1.0000 0.0066
-12.250 -0.8340 0.04788 0.04561 -0.0584 1.0000 0.0064
-12.000 -0.8584 0.03882 0.03636 -0.0672 1.0000 0.0064
-11.750 -0.8653 0.03483 0.03224 -0.0713 1.0000 0.0063
-11.500 -0.8743 0.02997 0.02707 -0.0746 1.0000 0.0064
-11.250 -0.8692 0.02710 0.02396 -0.0751 1.0000 0.0065
-11.000 -0.8587 0.02490 0.02156 -0.0750 1.0000 0.0066
-10.750 -0.8437 0.02317 0.01966 -0.0748 0.9999 0.0067
-10.500 -0.8154 0.02162 0.01796 -0.0768 0.9981 0.0068
-10.250 -0.7860 0.02049 0.01671 -0.0785 0.9961 0.0070
-10.000 -0.7557 0.01951 0.01562 -0.0801 0.9943 0.0071
-9.750 -0.7271 0.01858 0.01458 -0.0812 0.9918 0.0073
-9.500 -0.6978 0.01765 0.01353 -0.0824 0.9892 0.0075
-9.250 -0.6677 0.01668 0.01244 -0.0837 0.9868 0.0076
-9.000 -0.6366 0.01580 0.01144 -0.0851 0.9849 0.0078
-8.750 -0.6049 0.01498 0.01051 -0.0865 0.9830 0.0080
-8.500 -0.5771 0.01428 0.00970 -0.0870 0.9783 0.0082
-8.250 -0.5470 0.01363 0.00896 -0.0879 0.9743 0.0084
-8.000 -0.5158 0.01301 0.00825 -0.0889 0.9708 0.0086
-7.750 -0.4870 0.01247 0.00763 -0.0894 0.9656 0.0088
-7.500 -0.4576 0.01198 0.00707 -0.0899 0.9597 0.0089
-7.250 -0.4282 0.01152 0.00652 -0.0904 0.9540 0.0090
-7.000 -0.4003 0.01111 0.00605 -0.0905 0.9463 0.0091
-6.750 -0.3722 0.01071 0.00559 -0.0907 0.9390 0.0092
-6.500 -0.3450 0.01011 0.00489 -0.0907 0.9305 0.0096
-6.250 -0.3176 0.00970 0.00439 -0.0906 0.9228 0.0099
-6.000 -0.2902 0.00936 0.00399 -0.0906 0.9153 0.0103
-5.750 -0.2626 0.00908 0.00367 -0.0905 0.9084 0.0108
-5.500 -0.2350 0.00884 0.00338 -0.0904 0.9014 0.0113
-5.250 -0.2072 0.00861 0.00310 -0.0903 0.8948 0.0119
-5.000 -0.1794 0.00841 0.00284 -0.0903 0.8874 0.0123
-4.750 -0.1514 0.00823 0.00261 -0.0902 0.8801 0.0127
-4.500 -0.1235 0.00802 0.00235 -0.0901 0.8715 0.0140
-4.250 -0.0956 0.00783 0.00214 -0.0901 0.8626 0.0157
-4.000 -0.0678 0.00765 0.00194 -0.0900 0.8528 0.0200
-3.750 -0.0402 0.00742 0.00174 -0.0899 0.8407 0.0348
-3.500 -0.0126 0.00730 0.00160 -0.0897 0.8267 0.0440
-3.250 0.0152 0.00718 0.00147 -0.0896 0.8126 0.0553
-3.000 0.0431 0.00707 0.00136 -0.0895 0.7995 0.0666
-2.750 0.0711 0.00699 0.00126 -0.0894 0.7866 0.0767
-2.500 0.0991 0.00690 0.00117 -0.0894 0.7737 0.0898
-2.250 0.1271 0.00683 0.00109 -0.0893 0.7613 0.1027
-2.000 0.1551 0.00672 0.00101 -0.0893 0.7491 0.1247
-1.750 0.1832 0.00660 0.00095 -0.0893 0.7366 0.1547
-1.500 0.2112 0.00649 0.00089 -0.0893 0.7233 0.1874
-1.250 0.2393 0.00638 0.00084 -0.0893 0.7096 0.2242
-1.000 0.2672 0.00620 0.00079 -0.0894 0.6945 0.2869
-0.750 0.2950 0.00598 0.00076 -0.0895 0.6785 0.3717
-0.500 0.3229 0.00590 0.00076 -0.0895 0.6605 0.4235
-0.250 0.3506 0.00588 0.00078 -0.0894 0.6398 0.4614
0.000 0.3782 0.00593 0.00080 -0.0892 0.6180 0.4857
0.250 0.4057 0.00600 0.00083 -0.0891 0.5932 0.5115
0.500 0.4331 0.00610 0.00088 -0.0889 0.5656 0.5288
0.750 0.4602 0.00621 0.00094 -0.0887 0.5354 0.5560
1.000 0.4872 0.00634 0.00103 -0.0885 0.5041 0.5875
1.250 0.5142 0.00648 0.00112 -0.0883 0.4735 0.6125
1.500 0.5411 0.00665 0.00122 -0.0881 0.4419 0.6329
1.750 0.5681 0.00684 0.00132 -0.0878 0.4115 0.6469
2.000 0.5948 0.00706 0.00144 -0.0876 0.3782 0.6588
2.250 0.6212 0.00733 0.00157 -0.0873 0.3402 0.6701
2.500 0.6479 0.00756 0.00170 -0.0871 0.3108 0.6815
2.750 0.6746 0.00778 0.00183 -0.0869 0.2842 0.6936
3.000 0.7017 0.00794 0.00196 -0.0867 0.2651 0.7057
3.250 0.7287 0.00811 0.00210 -0.0865 0.2474 0.7182
3.500 0.7551 0.00835 0.00226 -0.0862 0.2238 0.7309
3.750 0.7813 0.00861 0.00245 -0.0859 0.1973 0.7444
4.000 0.8074 0.00889 0.00264 -0.0856 0.1712 0.7583
4.250 0.8334 0.00915 0.00286 -0.0853 0.1488 0.7733
4.500 0.8591 0.00945 0.00309 -0.0849 0.1262 0.7893
4.750 0.8847 0.00974 0.00333 -0.0845 0.1054 0.8073
5.000 0.9098 0.01004 0.00359 -0.0840 0.0865 0.8287
5.250 0.9344 0.01025 0.00384 -0.0833 0.0745 0.8614
5.500 0.9585 0.01026 0.00403 -0.0824 0.0667 1.0000
5.750 0.9847 0.01055 0.00428 -0.0822 0.0596 1.0000
6.000 1.0107 0.01086 0.00454 -0.0819 0.0527 1.0000
6.250 1.0369 0.01113 0.00481 -0.0816 0.0480 1.0000
6.500 1.0629 0.01142 0.00509 -0.0813 0.0441 1.0000
6.750 1.0885 0.01175 0.00540 -0.0809 0.0397 1.0000
7.000 1.1145 0.01201 0.00568 -0.0806 0.0377 1.0000
7.250 1.1400 0.01233 0.00599 -0.0802 0.0350 1.0000
7.500 1.1652 0.01268 0.00634 -0.0798 0.0321 1.0000
7.750 1.1904 0.01302 0.00668 -0.0794 0.0301 1.0000
8.000 1.2156 0.01333 0.00701 -0.0790 0.0284 1.0000
8.250 1.2403 0.01370 0.00738 -0.0785 0.0259 1.0000
8.500 1.2645 0.01411 0.00780 -0.0780 0.0238 1.0000
8.750 1.2890 0.01448 0.00819 -0.0775 0.0228 1.0000
9.000 1.3134 0.01483 0.00858 -0.0770 0.0217 1.0000
9.250 1.3373 0.01522 0.00898 -0.0765 0.0202 1.0000
9.500 1.3606 0.01568 0.00944 -0.0758 0.0185 1.0000
9.750 1.3836 0.01614 0.00994 -0.0752 0.0172 1.0000
10.000 1.4068 0.01656 0.01040 -0.0745 0.0164 1.0000
10.250 1.4294 0.01702 0.01089 -0.0738 0.0152 1.0000
10.500 1.4513 0.01755 0.01142 -0.0730 0.0138 1.0000
10.750 1.4727 0.01809 0.01200 -0.0721 0.0127 1.0000
11.000 1.4939 0.01861 0.01258 -0.0712 0.0118 1.0000
11.250 1.5142 0.01921 0.01320 -0.0702 0.0106 1.0000
11.500 1.5334 0.01988 0.01390 -0.0691 0.0094 1.0000
11.750 1.5526 0.02049 0.01457 -0.0680 0.0086 1.0000
12.000 1.5705 0.02118 0.01531 -0.0667 0.0078 1.0000
12.250 1.5869 0.02195 0.01612 -0.0652 0.0071 1.0000
12.500 1.6024 0.02273 0.01696 -0.0636 0.0066 1.0000
12.750 1.6159 0.02347 0.01778 -0.0616 0.0063 1.0000
13.000 1.6265 0.02426 0.01865 -0.0592 0.0060 1.0000
13.250 1.6358 0.02513 0.01959 -0.0568 0.0057 1.0000
13.500 1.6438 0.02611 0.02064 -0.0543 0.0055 1.0000
13.750 1.6508 0.02721 0.02182 -0.0520 0.0052 1.0000
14.000 1.6564 0.02847 0.02316 -0.0497 0.0050 1.0000
14.250 1.6608 0.02989 0.02468 -0.0475 0.0048 1.0000
14.500 1.6635 0.03153 0.02642 -0.0454 0.0046 1.0000
14.750 1.6680 0.03310 0.02809 -0.0438 0.0045 1.0000
15.000 1.6712 0.03488 0.02997 -0.0423 0.0044 1.0000
15.250 1.6732 0.03686 0.03207 -0.0410 0.0043 1.0000
15.500 1.6742 0.03906 0.03439 -0.0399 0.0042 1.0000
15.750 1.6734 0.04159 0.03703 -0.0392 0.0042 1.0000
16.000 1.6713 0.04440 0.03995 -0.0387 0.0041 1.0000
16.250 1.6675 0.04761 0.04329 -0.0387 0.0040 1.0000
16.500 1.6621 0.05122 0.04702 -0.0390 0.0039 1.0000
16.750 1.6541 0.05543 0.05137 -0.0399 0.0038 1.0000
17.000 1.6442 0.06020 0.05628 -0.0414 0.0038 1.0000
17.250 1.6318 0.06570 0.06192 -0.0436 0.0037 1.0000
17.500 1.6169 0.07204 0.06841 -0.0465 0.0037 1.0000
17.750 1.5988 0.07935 0.07588 -0.0502 0.0037 1.0000
18.000 1.5766 0.08784 0.08455 -0.0549 0.0037 1.0000
18.250 1.5505 0.09748 0.09436 -0.0603 0.0037 1.0000
18.500 1.5201 0.10833 0.10540 -0.0666 0.0037 1.0000
18.750 1.4865 0.12021 0.11746 -0.0737 0.0038 1.0000
19.000 1.4501 0.13309 0.13053 -0.0816 0.0038 1.0000
19.250 1.4142 0.14633 0.14394 -0.0899 0.0039 1.0000
|
Polar data table (+)
Polar graphs
<< Back to S2046 (s2046-il)