Dayton-Wright 6 (daytonwright6-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: Dayton-Wright 6 (daytonwright6-il) Reynolds number: 100,000 Max Cl/Cd: 49.75 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-daytonwright6-il-100000-n5.txt Download as CSV file: xf-daytonwright6-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: Dayton-Wright 6
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.2853 0.13279 0.12762 -0.0406 1.0000 0.0721
-12.750 -0.2947 0.13068 0.12558 -0.0418 1.0000 0.0724
-12.500 -0.3004 0.12815 0.12311 -0.0423 1.0000 0.0726
-12.250 -0.3052 0.12556 0.12058 -0.0423 1.0000 0.0726
-11.250 -0.2996 0.11457 0.10981 -0.0359 1.0000 0.0744
-10.750 -0.2708 0.10789 0.10311 -0.0400 0.9938 0.0773
-10.250 -0.2777 0.09158 0.08674 -0.0561 0.9789 0.0533
-10.000 -0.2631 0.08786 0.08300 -0.0593 0.9734 0.0527
-9.750 -0.2566 0.08381 0.07896 -0.0628 0.9650 0.0523
-9.500 -0.2542 0.07912 0.07427 -0.0677 0.9558 0.0522
-9.250 -0.2539 0.07363 0.06874 -0.0736 0.9463 0.0523
-9.000 -0.2530 0.06858 0.06364 -0.0773 0.9348 0.0521
-8.750 -0.2509 0.06335 0.05830 -0.0808 0.9247 0.0519
-8.500 -0.2430 0.05732 0.05209 -0.0849 0.9174 0.0513
-8.250 -0.2437 0.05176 0.04628 -0.0860 0.9066 0.0508
-8.000 -0.2355 0.04488 0.03894 -0.0885 0.9007 0.0504
-7.750 -0.2345 0.04052 0.03415 -0.0868 0.8898 0.0504
-7.500 -0.2156 0.03607 0.02912 -0.0876 0.8848 0.0507
-7.250 -0.2061 0.03351 0.02611 -0.0852 0.8745 0.0516
-7.000 -0.1793 0.03065 0.02264 -0.0858 0.8696 0.0529
-6.750 -0.1618 0.02884 0.02038 -0.0840 0.8603 0.0536
-6.500 -0.1301 0.02724 0.01858 -0.0849 0.8546 0.0543
-6.250 -0.1046 0.02612 0.01730 -0.0844 0.8463 0.0550
-6.000 -0.0736 0.02499 0.01600 -0.0849 0.8390 0.0561
-5.750 -0.0445 0.02399 0.01483 -0.0849 0.8309 0.0573
-5.500 -0.0137 0.02301 0.01368 -0.0852 0.8223 0.0588
-5.250 0.0142 0.02218 0.01268 -0.0849 0.8124 0.0607
-5.000 0.0476 0.02139 0.01178 -0.0857 0.8037 0.0637
-4.750 0.0715 0.02092 0.01129 -0.0847 0.7914 0.0668
-4.500 0.0994 0.02032 0.01058 -0.0843 0.7799 0.0705
-4.250 0.1300 0.01964 0.00983 -0.0845 0.7688 0.0750
-4.000 0.1526 0.01920 0.00936 -0.0832 0.7541 0.0816
-3.750 0.1759 0.01874 0.00889 -0.0820 0.7391 0.0916
-3.500 0.2002 0.01837 0.00852 -0.0810 0.7237 0.1065
-3.250 0.2253 0.01809 0.00821 -0.0802 0.7083 0.1247
-3.000 0.2511 0.01787 0.00792 -0.0795 0.6930 0.1435
-2.750 0.2772 0.01764 0.00769 -0.0790 0.6779 0.1641
-2.500 0.3037 0.01744 0.00748 -0.0786 0.6636 0.1893
-2.250 0.3305 0.01724 0.00728 -0.0782 0.6500 0.2167
-2.000 0.3579 0.01704 0.00706 -0.0780 0.6372 0.2464
-1.750 0.3858 0.01685 0.00688 -0.0779 0.6249 0.2840
-1.500 0.5223 0.01520 0.00698 -0.0999 0.6070 0.9221
-1.250 0.5864 0.01560 0.00707 -0.1071 0.5929 0.9937
-1.000 0.6208 0.01576 0.00702 -0.1086 0.5812 1.0000
-0.750 0.6423 0.01593 0.00700 -0.1073 0.5715 1.0000
-0.500 0.6630 0.01611 0.00702 -0.1060 0.5616 1.0000
-0.250 0.6841 0.01631 0.00707 -0.1047 0.5525 1.0000
0.000 0.7052 0.01651 0.00713 -0.1034 0.5438 1.0000
0.250 0.7260 0.01672 0.00723 -0.1021 0.5351 1.0000
0.500 0.7470 0.01694 0.00733 -0.1009 0.5267 1.0000
0.750 0.7675 0.01717 0.00746 -0.0995 0.5182 1.0000
1.000 0.7883 0.01741 0.00760 -0.0982 0.5102 1.0000
1.250 0.8090 0.01765 0.00776 -0.0969 0.5024 1.0000
1.500 0.8293 0.01790 0.00794 -0.0956 0.4945 1.0000
1.750 0.8501 0.01816 0.00812 -0.0943 0.4872 1.0000
2.000 0.8696 0.01842 0.00834 -0.0928 0.4790 1.0000
2.250 0.8907 0.01869 0.00852 -0.0917 0.4723 1.0000
2.500 0.9096 0.01897 0.00881 -0.0901 0.4644 1.0000
2.750 0.9307 0.01924 0.00900 -0.0890 0.4582 1.0000
3.000 0.9496 0.01955 0.00931 -0.0874 0.4508 1.0000
3.250 0.9692 0.01984 0.00957 -0.0860 0.4440 1.0000
3.500 0.9890 0.02015 0.00985 -0.0847 0.4376 1.0000
3.750 1.0077 0.02047 0.01018 -0.0832 0.4308 1.0000
4.000 1.0286 0.02078 0.01043 -0.0821 0.4255 1.0000
4.250 1.0465 0.02114 0.01084 -0.0804 0.4190 1.0000
4.500 1.0654 0.02148 0.01117 -0.0790 0.4129 1.0000
4.750 1.0855 0.02182 0.01148 -0.0778 0.4077 1.0000
5.000 1.1026 0.02221 0.01195 -0.0761 0.4015 1.0000
5.250 1.1216 0.02258 0.01231 -0.0748 0.3963 1.0000
5.500 1.1414 0.02296 0.01267 -0.0736 0.3915 1.0000
5.750 1.1575 0.02340 0.01321 -0.0718 0.3857 1.0000
6.000 1.1757 0.02380 0.01363 -0.0704 0.3807 1.0000
6.250 1.1962 0.02420 0.01399 -0.0694 0.3764 1.0000
6.500 1.2103 0.02471 0.01463 -0.0673 0.3710 1.0000
6.750 1.2271 0.02517 0.01514 -0.0657 0.3660 1.0000
7.000 1.2473 0.02558 0.01553 -0.0648 0.3619 1.0000
7.250 1.2607 0.02615 0.01621 -0.0627 0.3571 1.0000
7.500 1.2736 0.02667 0.01683 -0.0604 0.3522 1.0000
7.750 1.2905 0.02714 0.01734 -0.0590 0.3480 1.0000
8.000 1.3087 0.02765 0.01787 -0.0578 0.3441 1.0000
8.250 1.3165 0.02831 0.01869 -0.0549 0.3393 1.0000
8.500 1.3293 0.02888 0.01935 -0.0528 0.3348 1.0000
8.750 1.3475 0.02930 0.01976 -0.0517 0.3299 1.0000
9.000 1.3498 0.03005 0.02068 -0.0482 0.3240 1.0000
9.250 1.3566 0.03063 0.02132 -0.0454 0.3174 1.0000
9.500 1.3651 0.03123 0.02196 -0.0430 0.3111 1.0000
9.750 1.3661 0.03212 0.02300 -0.0398 0.3042 1.0000
10.000 1.3773 0.03266 0.02352 -0.0380 0.2979 1.0000
10.250 1.3763 0.03387 0.02494 -0.0350 0.2919 1.0000
10.500 1.3790 0.03485 0.02600 -0.0325 0.2849 1.0000
10.750 1.3800 0.03606 0.02731 -0.0302 0.2781 1.0000
11.000 1.3801 0.03746 0.02886 -0.0280 0.2716 1.0000
11.250 1.3851 0.03861 0.03003 -0.0263 0.2658 1.0000
11.500 1.3800 0.04061 0.03225 -0.0242 0.2589 1.0000
11.750 1.3798 0.04218 0.03385 -0.0225 0.2514 1.0000
12.000 1.3708 0.04481 0.03670 -0.0208 0.2437 1.0000
12.250 1.3684 0.04688 0.03881 -0.0196 0.2367 1.0000
12.500 1.3593 0.04996 0.04210 -0.0186 0.2300 1.0000
12.750 1.3531 0.05279 0.04500 -0.0178 0.2229 1.0000
13.000 1.3387 0.05683 0.04922 -0.0175 0.2150 1.0000
13.250 1.3280 0.06057 0.05301 -0.0173 0.2071 1.0000
13.500 1.3107 0.06554 0.05816 -0.0177 0.1999 1.0000
13.750 1.2971 0.07007 0.06276 -0.0181 0.1923 1.0000
14.000 1.2782 0.07564 0.06849 -0.0190 0.1857 1.0000
14.250 1.2617 0.08090 0.07381 -0.0199 0.1773 1.0000
14.500 1.2440 0.08657 0.07959 -0.0210 0.1706 1.0000
14.750 1.2269 0.09221 0.08530 -0.0223 0.1616 1.0000
15.000 1.2140 0.09730 0.09042 -0.0234 0.1528 1.0000
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Polar data table (+)
Polar graphs
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