Dayton-Wright 6 (daytonwright6-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: Dayton-Wright 6 (daytonwright6-il) Reynolds number: 50,000 Max Cl/Cd: 31.1 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-daytonwright6-il-50000-n5.txt Download as CSV file: xf-daytonwright6-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3118 0.10999 0.10366 -0.0273 1.0000 0.1376
-9.500 -0.3227 0.10809 0.10184 -0.0258 1.0000 0.1366
-9.000 -0.3639 0.09605 0.08981 -0.0365 0.9890 0.0838
-8.750 -0.3477 0.09197 0.08570 -0.0398 0.9814 0.0822
-8.500 -0.3348 0.08733 0.08102 -0.0446 0.9726 0.0805
-8.250 -0.3256 0.08252 0.07615 -0.0491 0.9620 0.0791
-8.000 -0.3165 0.07774 0.07129 -0.0533 0.9510 0.0785
-7.750 -0.3058 0.07318 0.06661 -0.0570 0.9404 0.0789
-7.500 -0.2894 0.06826 0.06150 -0.0613 0.9316 0.0791
-7.250 -0.2801 0.06402 0.05708 -0.0630 0.9198 0.0788
-7.000 -0.2677 0.05968 0.05246 -0.0647 0.9090 0.0782
-6.750 -0.2469 0.05494 0.04735 -0.0674 0.9009 0.0777
-6.500 -0.2345 0.05142 0.04349 -0.0672 0.8890 0.0776
-6.250 -0.2157 0.04806 0.03974 -0.0676 0.8792 0.0779
-6.000 -0.1912 0.04489 0.03613 -0.0684 0.8706 0.0787
-5.750 -0.1720 0.04255 0.03338 -0.0677 0.8593 0.0805
-5.500 -0.1401 0.03974 0.02995 -0.0689 0.8528 0.0833
-5.250 -0.1202 0.03784 0.02759 -0.0676 0.8408 0.0853
-5.000 -0.0871 0.03622 0.02580 -0.0686 0.8333 0.0874
-4.750 -0.0597 0.03489 0.02425 -0.0684 0.8228 0.0901
-4.500 -0.0302 0.03357 0.02265 -0.0684 0.8130 0.0934
-4.250 0.0072 0.03213 0.02084 -0.0696 0.8049 0.0993
-4.000 0.0337 0.03147 0.02019 -0.0692 0.7932 0.1064
-3.750 0.0781 0.03024 0.01879 -0.0716 0.7866 0.1181
-3.500 0.1074 0.02955 0.01798 -0.0716 0.7740 0.1314
-3.250 0.1427 0.02891 0.01729 -0.0726 0.7637 0.1528
-3.000 0.1785 0.02833 0.01673 -0.0738 0.7541 0.1862
-2.750 0.2034 0.02800 0.01639 -0.0731 0.7411 0.2154
-2.500 0.2335 0.02745 0.01585 -0.0732 0.7297 0.2423
-2.250 0.2703 0.02666 0.01509 -0.0743 0.7209 0.2750
-2.000 0.2929 0.02627 0.01482 -0.0732 0.7080 0.3128
-1.750 0.4489 0.02351 0.01391 -0.0969 0.6991 1.0000
-1.500 0.4790 0.02341 0.01342 -0.0969 0.6883 1.0000
-1.250 0.4996 0.02356 0.01332 -0.0954 0.6753 1.0000
-1.000 0.5220 0.02369 0.01321 -0.0942 0.6633 1.0000
-0.750 0.5483 0.02375 0.01300 -0.0937 0.6528 1.0000
-0.500 0.5744 0.02382 0.01284 -0.0931 0.6421 1.0000
-0.250 0.5952 0.02408 0.01292 -0.0917 0.6306 1.0000
0.000 0.6212 0.02422 0.01285 -0.0912 0.6207 1.0000
0.250 0.6452 0.02443 0.01288 -0.0904 0.6104 1.0000
0.500 0.6659 0.02476 0.01307 -0.0891 0.5998 1.0000
0.750 0.6957 0.02488 0.01297 -0.0892 0.5911 1.0000
1.000 0.7120 0.02536 0.01339 -0.0873 0.5803 1.0000
1.250 0.7371 0.02565 0.01354 -0.0868 0.5716 1.0000
1.500 0.7575 0.02606 0.01386 -0.0855 0.5619 1.0000
1.750 0.7790 0.02647 0.01418 -0.0845 0.5529 1.0000
2.000 0.8014 0.02687 0.01449 -0.0835 0.5442 1.0000
2.250 0.8208 0.02737 0.01494 -0.0822 0.5357 1.0000
2.500 0.8427 0.02781 0.01530 -0.0813 0.5274 1.0000
2.750 0.8617 0.02835 0.01581 -0.0799 0.5193 1.0000
3.000 0.8816 0.02887 0.01629 -0.0787 0.5112 1.0000
3.250 0.9026 0.02939 0.01677 -0.0777 0.5040 1.0000
3.500 0.9178 0.03007 0.01746 -0.0758 0.4960 1.0000
3.750 0.9456 0.03041 0.01772 -0.0758 0.4898 1.0000
4.000 0.9520 0.03138 0.01878 -0.0727 0.4816 1.0000
4.250 0.9773 0.03180 0.01916 -0.0724 0.4755 1.0000
4.500 0.9869 0.03273 0.02017 -0.0698 0.4683 1.0000
4.750 1.0033 0.03343 0.02090 -0.0683 0.4617 1.0000
5.000 1.0292 0.03386 0.02128 -0.0681 0.4564 1.0000
5.250 1.0286 0.03517 0.02274 -0.0642 0.4490 1.0000
5.500 1.0503 0.03574 0.02332 -0.0635 0.4436 1.0000
5.750 1.0618 0.03669 0.02433 -0.0614 0.4378 1.0000
6.000 1.0633 0.03799 0.02574 -0.0580 0.4313 1.0000
6.250 1.0891 0.03840 0.02615 -0.0578 0.4265 1.0000
6.500 1.0841 0.04000 0.02788 -0.0537 0.4205 1.0000
6.750 1.0805 0.04154 0.02951 -0.0498 0.4146 1.0000
7.000 1.1099 0.04179 0.02978 -0.0501 0.4102 1.0000
7.250 1.0841 0.04448 0.03261 -0.0442 0.4038 1.0000
7.500 1.0781 0.04651 0.03473 -0.0409 0.3978 1.0000
7.750 1.1117 0.04643 0.03469 -0.0414 0.3941 1.0000
8.000 1.0365 0.05348 0.04189 -0.0341 0.3843 1.0000
8.250 1.0549 0.05422 0.04269 -0.0334 0.3800 1.0000
8.500 1.0993 0.05298 0.04152 -0.0339 0.3775 1.0000
8.750 0.9986 0.06476 0.05338 -0.0297 0.3638 1.0000
9.000 1.0349 0.06356 0.05227 -0.0292 0.3617 1.0000
9.500 0.9848 0.07537 0.06421 -0.0283 0.3449 1.0000
10.000 0.9527 0.08629 0.07527 -0.0289 0.3286 1.0000
10.500 0.9349 0.09538 0.08450 -0.0295 0.3145 1.0000
11.000 0.9139 0.10503 0.09428 -0.0307 0.3002 1.0000
11.250 0.9377 0.10509 0.09443 -0.0299 0.2979 1.0000
11.500 0.8994 0.11393 0.10331 -0.0321 0.2870 1.0000
11.750 0.9176 0.11476 0.10424 -0.0316 0.2837 1.0000
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Polar data table (+)
Polar graphs
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