DAE-51 AIRFOIL (dae51-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: DAE-51 AIRFOIL (dae51-il) Reynolds number: 1,000,000 Max Cl/Cd: 127.18 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-dae51-il-1000000-n5.txt Download as CSV file: xf-dae51-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: DAE-51 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4030 0.11085 0.10918 -0.0226 0.9716 0.0062
-8.000 -0.4269 0.01973 0.01600 -0.0956 0.8436 0.0073
-7.750 -0.4024 0.01763 0.01353 -0.0962 0.8380 0.0075
-7.500 -0.3764 0.01613 0.01177 -0.0967 0.8325 0.0077
-7.250 -0.3498 0.01500 0.01040 -0.0969 0.8269 0.0079
-7.000 -0.3229 0.01409 0.00930 -0.0972 0.8218 0.0081
-6.750 -0.2954 0.01335 0.00840 -0.0974 0.8163 0.0083
-6.500 -0.2678 0.01274 0.00764 -0.0975 0.8109 0.0084
-6.250 -0.2400 0.01219 0.00696 -0.0977 0.8059 0.0085
-6.000 -0.2121 0.01157 0.00622 -0.0979 0.8005 0.0087
-5.750 -0.1843 0.01089 0.00541 -0.0981 0.7951 0.0090
-5.500 -0.1561 0.01046 0.00490 -0.0982 0.7901 0.0092
-5.250 -0.1277 0.01011 0.00449 -0.0984 0.7845 0.0094
-4.750 -0.0709 0.00951 0.00376 -0.0987 0.7738 0.0100
-4.500 -0.0423 0.00925 0.00344 -0.0989 0.7679 0.0105
-4.250 -0.0138 0.00903 0.00316 -0.0990 0.7627 0.0110
-4.000 0.0149 0.00881 0.00290 -0.0992 0.7567 0.0114
-3.750 0.0436 0.00854 0.00255 -0.0994 0.7507 0.0120
-3.500 0.0723 0.00831 0.00230 -0.0995 0.7449 0.0129
-3.250 0.1011 0.00815 0.00210 -0.0997 0.7383 0.0137
-3.000 0.1298 0.00801 0.00192 -0.0999 0.7322 0.0148
-2.750 0.1586 0.00787 0.00174 -0.1000 0.7251 0.0160
-2.500 0.1873 0.00774 0.00159 -0.1002 0.7186 0.0180
-2.250 0.2162 0.00764 0.00147 -0.1003 0.7113 0.0201
-2.000 0.2449 0.00753 0.00135 -0.1005 0.7042 0.0250
-1.750 0.2737 0.00743 0.00125 -0.1007 0.6962 0.0318
-1.500 0.3024 0.00734 0.00117 -0.1009 0.6883 0.0431
-1.250 0.3311 0.00724 0.00110 -0.1011 0.6795 0.0611
-1.000 0.3598 0.00713 0.00104 -0.1013 0.6709 0.0866
-0.750 0.3884 0.00700 0.00099 -0.1015 0.6614 0.1328
-0.500 0.4171 0.00679 0.00097 -0.1018 0.6512 0.2046
-0.250 0.4457 0.00662 0.00096 -0.1021 0.6408 0.2804
0.000 0.4741 0.00648 0.00097 -0.1024 0.6295 0.3551
0.250 0.5025 0.00637 0.00099 -0.1026 0.6176 0.4234
0.500 0.5308 0.00620 0.00104 -0.1028 0.6051 0.5232
0.750 0.5589 0.00608 0.00110 -0.1030 0.5925 0.6078
1.000 0.5868 0.00599 0.00116 -0.1031 0.5796 0.6858
1.250 0.6140 0.00587 0.00124 -0.1029 0.5667 0.7720
1.500 0.6380 0.00568 0.00131 -0.1020 0.5539 0.8826
1.750 0.6652 0.00561 0.00132 -0.1017 0.5404 1.0000
2.000 0.6933 0.00575 0.00138 -0.1018 0.5264 1.0000
2.250 0.7214 0.00589 0.00145 -0.1018 0.5118 1.0000
2.500 0.7493 0.00604 0.00153 -0.1019 0.4968 1.0000
2.750 0.7771 0.00620 0.00162 -0.1020 0.4810 1.0000
3.000 0.8048 0.00637 0.00172 -0.1020 0.4643 1.0000
3.250 0.8324 0.00655 0.00183 -0.1020 0.4471 1.0000
3.500 0.8597 0.00676 0.00196 -0.1020 0.4286 1.0000
3.750 0.8869 0.00698 0.00209 -0.1020 0.4089 1.0000
4.000 0.9137 0.00723 0.00226 -0.1019 0.3855 1.0000
4.250 0.9403 0.00751 0.00243 -0.1018 0.3615 1.0000
4.500 0.9664 0.00784 0.00263 -0.1017 0.3330 1.0000
4.750 0.9914 0.00830 0.00290 -0.1014 0.2943 1.0000
5.000 1.0170 0.00868 0.00315 -0.1012 0.2658 1.0000
5.250 1.0421 0.00909 0.00342 -0.1009 0.2356 1.0000
5.500 1.0657 0.00968 0.00378 -0.1004 0.1924 1.0000
5.750 1.0900 0.01016 0.00411 -0.1000 0.1627 1.0000
6.000 1.1145 0.01061 0.00444 -0.0996 0.1387 1.0000
6.250 1.1383 0.01112 0.00481 -0.0992 0.1128 1.0000
6.500 1.1622 0.01160 0.00518 -0.0987 0.0914 1.0000
6.750 1.1859 0.01208 0.00558 -0.0982 0.0736 1.0000
7.000 1.2093 0.01258 0.00598 -0.0977 0.0570 1.0000
7.250 1.2324 0.01308 0.00641 -0.0971 0.0440 1.0000
7.500 1.2557 0.01355 0.00684 -0.0966 0.0348 1.0000
7.750 1.2791 0.01398 0.00725 -0.0960 0.0285 1.0000
8.000 1.3022 0.01442 0.00767 -0.0954 0.0238 1.0000
8.250 1.3248 0.01490 0.00813 -0.0948 0.0200 1.0000
8.500 1.3476 0.01531 0.00856 -0.0941 0.0177 1.0000
8.750 1.3694 0.01581 0.00906 -0.0934 0.0155 1.0000
9.000 1.3915 0.01626 0.00954 -0.0926 0.0142 1.0000
9.250 1.4130 0.01672 0.01003 -0.0918 0.0131 1.0000
9.500 1.4335 0.01726 0.01058 -0.0909 0.0120 1.0000
9.750 1.4530 0.01783 0.01120 -0.0898 0.0110 1.0000
10.000 1.4731 0.01832 0.01174 -0.0888 0.0105 1.0000
10.250 1.4920 0.01887 0.01232 -0.0876 0.0097 1.0000
10.500 1.5093 0.01947 0.01295 -0.0862 0.0091 1.0000
10.750 1.5232 0.02013 0.01365 -0.0842 0.0085 1.0000
11.000 1.5364 0.02087 0.01444 -0.0822 0.0080 1.0000
11.250 1.5505 0.02157 0.01521 -0.0805 0.0077 1.0000
11.500 1.5639 0.02234 0.01604 -0.0788 0.0074 1.0000
11.750 1.5765 0.02318 0.01695 -0.0770 0.0071 1.0000
12.000 1.5885 0.02411 0.01794 -0.0753 0.0068 1.0000
12.250 1.5997 0.02512 0.01901 -0.0737 0.0065 1.0000
12.500 1.6099 0.02623 0.02018 -0.0720 0.0063 1.0000
12.750 1.6189 0.02749 0.02150 -0.0704 0.0060 1.0000
13.000 1.6254 0.02899 0.02310 -0.0686 0.0057 1.0000
13.250 1.6336 0.03039 0.02458 -0.0671 0.0055 1.0000
13.500 1.6419 0.03182 0.02609 -0.0657 0.0054 1.0000
13.750 1.6491 0.03337 0.02773 -0.0644 0.0053 1.0000
14.000 1.6552 0.03508 0.02952 -0.0631 0.0052 1.0000
14.250 1.6602 0.03693 0.03146 -0.0619 0.0050 1.0000
14.500 1.6642 0.03891 0.03354 -0.0608 0.0049 1.0000
14.750 1.6675 0.04103 0.03575 -0.0598 0.0048 1.0000
15.000 1.6696 0.04335 0.03816 -0.0589 0.0047 1.0000
15.250 1.6705 0.04581 0.04072 -0.0580 0.0046 1.0000
15.500 1.6707 0.04845 0.04346 -0.0574 0.0045 1.0000
15.750 1.6696 0.05133 0.04644 -0.0569 0.0044 1.0000
16.000 1.6677 0.05441 0.04963 -0.0566 0.0043 1.0000
16.250 1.6645 0.05776 0.05308 -0.0565 0.0042 1.0000
16.500 1.6600 0.06144 0.05687 -0.0566 0.0042 1.0000
16.750 1.6541 0.06542 0.06096 -0.0570 0.0041 1.0000
17.000 1.6461 0.06979 0.06545 -0.0576 0.0040 1.0000
17.250 1.6364 0.07454 0.07032 -0.0584 0.0040 1.0000
17.500 1.6252 0.07968 0.07559 -0.0596 0.0039 1.0000
17.750 1.6118 0.08529 0.08133 -0.0611 0.0039 1.0000
18.000 1.5965 0.09133 0.08750 -0.0629 0.0038 1.0000
18.250 1.5802 0.09770 0.09401 -0.0651 0.0038 1.0000
18.500 1.5634 0.10433 0.10077 -0.0675 0.0038 1.0000
18.750 1.5458 0.11120 0.10777 -0.0701 0.0037 1.0000
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