Dayton-Wright 6 (daytonwright6-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: Dayton-Wright 6 (daytonwright6-il) Reynolds number: 200,000 Max Cl/Cd: 66.39 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-daytonwright6-il-200000-n5.txt Download as CSV file: xf-daytonwright6-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.2346 0.09132 0.08768 -0.0618 0.9772 0.0368
-10.750 -0.2270 0.08630 0.08266 -0.0667 0.9711 0.0371
-10.500 -0.2227 0.08135 0.07770 -0.0710 0.9621 0.0370
-10.250 -0.2213 0.07620 0.07256 -0.0754 0.9516 0.0369
-10.000 -0.2229 0.07033 0.06670 -0.0812 0.9413 0.0365
-9.500 -0.3136 0.03635 0.03159 -0.1030 0.9061 0.0352
-9.250 -0.3000 0.03205 0.02676 -0.1041 0.9005 0.0359
-9.000 -0.2908 0.02925 0.02352 -0.1025 0.8910 0.0363
-8.750 -0.2683 0.02670 0.02051 -0.1029 0.8855 0.0367
-8.500 -0.2503 0.02498 0.01844 -0.1017 0.8775 0.0370
-8.250 -0.2244 0.02340 0.01653 -0.1018 0.8714 0.0373
-8.000 -0.1992 0.02213 0.01498 -0.1015 0.8646 0.0377
-7.750 -0.1737 0.02108 0.01368 -0.1012 0.8571 0.0381
-7.500 -0.1442 0.02010 0.01247 -0.1016 0.8507 0.0385
-7.250 -0.1204 0.01936 0.01156 -0.1007 0.8422 0.0388
-6.750 -0.0680 0.01789 0.00991 -0.1000 0.8260 0.0403
-6.500 -0.0393 0.01731 0.00924 -0.1001 0.8181 0.0411
-6.250 -0.0164 0.01685 0.00872 -0.0989 0.8081 0.0419
-6.000 0.0093 0.01638 0.00815 -0.0983 0.7985 0.0426
-5.750 0.0339 0.01595 0.00763 -0.0975 0.7879 0.0434
-5.500 0.0565 0.01557 0.00718 -0.0962 0.7760 0.0441
-5.250 0.0800 0.01523 0.00675 -0.0951 0.7631 0.0450
-5.000 0.1031 0.01493 0.00634 -0.0938 0.7484 0.0459
-4.750 0.1251 0.01460 0.00597 -0.0924 0.7314 0.0474
-4.500 0.1477 0.01435 0.00565 -0.0911 0.7129 0.0490
-4.250 0.1707 0.01414 0.00534 -0.0899 0.6926 0.0514
-4.000 0.1937 0.01394 0.00505 -0.0887 0.6723 0.0557
-3.750 0.2162 0.01379 0.00482 -0.0874 0.6527 0.0632
-3.500 0.2385 0.01367 0.00463 -0.0861 0.6348 0.0749
-3.250 0.2607 0.01359 0.00448 -0.0848 0.6188 0.0892
-3.000 0.2831 0.01355 0.00437 -0.0835 0.6047 0.1032
-2.500 0.3284 0.01352 0.00424 -0.0813 0.5801 0.1310
-2.250 0.3512 0.01351 0.00420 -0.0802 0.5700 0.1466
-2.000 0.3738 0.01350 0.00418 -0.0791 0.5602 0.1640
-1.750 0.3963 0.01346 0.00416 -0.0780 0.5509 0.1856
-1.250 0.4402 0.01335 0.00417 -0.0756 0.5342 0.2494
-1.000 0.4611 0.01325 0.00419 -0.0743 0.5266 0.3026
-0.750 0.5865 0.01199 0.00466 -0.0953 0.5131 0.9167
-0.500 0.6305 0.01232 0.00485 -0.0985 0.5044 0.9625
-0.250 0.6750 0.01260 0.00502 -0.1020 0.4953 0.9873
0.000 0.7321 0.01281 0.00508 -0.1085 0.4865 1.0000
0.250 0.7519 0.01293 0.00513 -0.1070 0.4791 1.0000
0.500 0.7714 0.01308 0.00519 -0.1054 0.4722 1.0000
0.750 0.7912 0.01320 0.00526 -0.1039 0.4644 1.0000
1.000 0.8105 0.01337 0.00534 -0.1023 0.4577 1.0000
1.250 0.8306 0.01350 0.00544 -0.1008 0.4505 1.0000
1.500 0.8500 0.01366 0.00555 -0.0992 0.4437 1.0000
1.750 0.8696 0.01383 0.00566 -0.0977 0.4367 1.0000
2.000 0.8888 0.01400 0.00579 -0.0961 0.4295 1.0000
2.250 0.9077 0.01419 0.00593 -0.0945 0.4227 1.0000
2.500 0.9270 0.01436 0.00608 -0.0929 0.4155 1.0000
2.750 0.9454 0.01458 0.00623 -0.0912 0.4093 1.0000
3.000 0.9650 0.01477 0.00642 -0.0897 0.4029 1.0000
3.250 0.9835 0.01499 0.00660 -0.0880 0.3966 1.0000
3.500 1.0018 0.01522 0.00680 -0.0863 0.3906 1.0000
3.750 1.0205 0.01544 0.00701 -0.0847 0.3843 1.0000
4.000 1.0382 0.01570 0.00723 -0.0829 0.3788 1.0000
4.250 1.0567 0.01595 0.00748 -0.0814 0.3735 1.0000
4.500 1.0749 0.01619 0.00773 -0.0797 0.3680 1.0000
4.750 1.0921 0.01648 0.00798 -0.0779 0.3631 1.0000
5.000 1.1095 0.01675 0.00826 -0.0761 0.3582 1.0000
5.250 1.1264 0.01701 0.00854 -0.0743 0.3533 1.0000
5.500 1.1422 0.01729 0.00881 -0.0722 0.3488 1.0000
5.750 1.1578 0.01761 0.00911 -0.0702 0.3445 1.0000
6.000 1.1749 0.01788 0.00944 -0.0684 0.3400 1.0000
6.250 1.1913 0.01818 0.00977 -0.0666 0.3356 1.0000
6.500 1.2071 0.01853 0.01010 -0.0647 0.3314 1.0000
6.750 1.2239 0.01888 0.01048 -0.0631 0.3276 1.0000
7.000 1.2403 0.01920 0.01088 -0.0614 0.3228 1.0000
7.250 1.2551 0.01957 0.01127 -0.0595 0.3178 1.0000
7.500 1.2688 0.01999 0.01167 -0.0574 0.3122 1.0000
7.750 1.2823 0.02036 0.01213 -0.0553 0.3053 1.0000
8.000 1.2944 0.02083 0.01259 -0.0531 0.2991 1.0000
8.250 1.3085 0.02127 0.01310 -0.0514 0.2933 1.0000
8.500 1.3215 0.02175 0.01363 -0.0495 0.2871 1.0000
8.750 1.3332 0.02232 0.01421 -0.0474 0.2818 1.0000
9.000 1.3461 0.02284 0.01484 -0.0457 0.2745 1.0000
9.250 1.3553 0.02352 0.01552 -0.0435 0.2673 1.0000
9.500 1.3674 0.02414 0.01624 -0.0419 0.2597 1.0000
9.750 1.3765 0.02492 0.01705 -0.0399 0.2527 1.0000
10.000 1.3869 0.02570 0.01791 -0.0382 0.2439 1.0000
10.250 1.3941 0.02667 0.01891 -0.0363 0.2363 1.0000
10.500 1.3996 0.02779 0.02005 -0.0343 0.2232 1.0000
10.750 1.4024 0.02916 0.02142 -0.0323 0.2086 1.0000
11.000 1.4049 0.03064 0.02291 -0.0304 0.1949 1.0000
11.250 1.4034 0.03250 0.02473 -0.0285 0.1792 1.0000
11.500 1.3994 0.03466 0.02686 -0.0265 0.1625 1.0000
11.750 1.3868 0.03768 0.02979 -0.0244 0.1404 1.0000
12.000 1.3738 0.04099 0.03303 -0.0228 0.1201 1.0000
12.250 1.3585 0.04477 0.03674 -0.0215 0.1015 1.0000
12.500 1.3430 0.04886 0.04081 -0.0206 0.0844 1.0000
12.750 1.3155 0.05456 0.04640 -0.0201 0.0597 1.0000
13.000 1.2901 0.06038 0.05216 -0.0201 0.0391 1.0000
13.250 1.2710 0.06566 0.05745 -0.0204 0.0298 1.0000
13.500 1.2574 0.07042 0.06228 -0.0209 0.0260 1.0000
13.750 1.2474 0.07483 0.06677 -0.0214 0.0243 1.0000
14.000 1.2373 0.07934 0.07139 -0.0221 0.0228 1.0000
14.250 1.2274 0.08391 0.07606 -0.0228 0.0219 1.0000
14.500 1.2200 0.08821 0.08048 -0.0237 0.0214 1.0000
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Polar data table (+)
Polar graphs
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