Dayton-Wright 6 (daytonwright6-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: Dayton-Wright 6 (daytonwright6-il) Reynolds number: 100,000 Max Cl/Cd: 45.62 at α=2° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-daytonwright6-il-100000.txt Download as CSV file: xf-daytonwright6-il-100000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3499 0.10508 0.10088 -0.0201 1.0000 0.1181
-9.000 -0.3705 0.10396 0.09985 -0.0188 1.0000 0.1196
-8.750 -0.4060 0.10228 0.09821 -0.0306 0.9898 0.1219
-8.500 -0.3761 0.09654 0.09248 -0.0297 0.9861 0.1242
-8.250 -0.3413 0.09278 0.08871 -0.0308 0.9813 0.1278
-8.000 -0.3232 0.08886 0.08476 -0.0368 0.9720 0.1330
-7.750 -0.3211 0.08301 0.07875 -0.0504 0.9566 0.1391
-7.500 -0.2964 0.07959 0.07537 -0.0491 0.9488 0.1413
-7.250 -0.2662 0.07597 0.07172 -0.0525 0.9417 0.1466
-7.000 -0.1595 0.05920 0.05515 -0.0633 0.9036 0.1624
-6.750 -0.2310 0.06807 0.06365 -0.0604 0.9182 0.1591
-6.500 -0.2147 0.06475 0.06002 -0.0657 0.9049 0.1723
-6.250 -0.1792 0.06102 0.05638 -0.0670 0.8996 0.1767
-6.000 -0.1618 0.05805 0.05314 -0.0698 0.8862 0.1900
-5.750 -0.1217 0.05429 0.04940 -0.0726 0.8821 0.1955
-5.500 -0.1166 0.04109 0.03455 -0.0745 0.8681 0.1046
-5.250 -0.0946 0.03786 0.03094 -0.0738 0.8570 0.1010
-5.000 -0.0560 0.03457 0.02714 -0.0756 0.8514 0.1009
-4.750 -0.0295 0.03238 0.02453 -0.0749 0.8405 0.1014
-4.500 0.0155 0.02974 0.02139 -0.0772 0.8354 0.1023
-4.250 0.0665 0.02750 0.01866 -0.0805 0.8310 0.1054
-4.000 0.0978 0.02607 0.01708 -0.0805 0.8193 0.1101
-3.750 0.1358 0.02502 0.01592 -0.0817 0.8096 0.1197
-3.500 0.1804 0.02353 0.01437 -0.0840 0.8016 0.1340
-3.250 0.2107 0.02250 0.01340 -0.0838 0.7895 0.1587
-3.000 0.2566 0.02138 0.01234 -0.0865 0.7823 0.1988
-2.750 0.2800 0.02098 0.01196 -0.0853 0.7685 0.2262
-2.500 0.3059 0.02058 0.01165 -0.0846 0.7558 0.2592
-2.250 0.5482 0.01661 0.00982 -0.1253 0.7487 1.0000
-2.000 0.5685 0.01665 0.00961 -0.1237 0.7337 1.0000
-1.750 0.5889 0.01669 0.00943 -0.1220 0.7194 1.0000
-1.500 0.6100 0.01675 0.00929 -0.1206 0.7058 1.0000
-1.250 0.6327 0.01680 0.00914 -0.1194 0.6932 1.0000
-1.000 0.6578 0.01683 0.00895 -0.1186 0.6815 1.0000
-0.750 0.6810 0.01692 0.00885 -0.1175 0.6692 1.0000
-0.500 0.7009 0.01711 0.00890 -0.1159 0.6565 1.0000
-0.250 0.7231 0.01730 0.00894 -0.1148 0.6449 1.0000
0.000 0.7496 0.01746 0.00888 -0.1144 0.6343 1.0000
0.250 0.7692 0.01774 0.00907 -0.1128 0.6223 1.0000
0.500 0.7896 0.01806 0.00927 -0.1114 0.6109 1.0000
0.750 0.8156 0.01832 0.00935 -0.1110 0.6009 1.0000
1.000 0.8345 0.01869 0.00965 -0.1093 0.5898 1.0000
1.250 0.8552 0.01908 0.00996 -0.1080 0.5798 1.0000
1.500 0.8808 0.01940 0.01012 -0.1076 0.5703 1.0000
1.750 0.8969 0.01987 0.01059 -0.1055 0.5599 1.0000
2.000 0.9234 0.02024 0.01080 -0.1052 0.5514 1.0000
2.250 0.9389 0.02073 0.01134 -0.1031 0.5419 1.0000
2.500 0.9643 0.02116 0.01163 -0.1027 0.5341 1.0000
2.750 0.9800 0.02166 0.01218 -0.1006 0.5250 1.0000
3.000 1.0059 0.02209 0.01249 -0.1003 0.5177 1.0000
3.250 1.0199 0.02266 0.01314 -0.0980 0.5092 1.0000
3.500 1.0480 0.02307 0.01341 -0.0981 0.5029 1.0000
3.750 1.0593 0.02374 0.01421 -0.0954 0.4950 1.0000
4.000 1.0830 0.02416 0.01459 -0.0948 0.4883 1.0000
4.250 1.1008 0.02479 0.01525 -0.0932 0.4817 1.0000
4.500 1.1174 0.02539 0.01590 -0.0914 0.4748 1.0000
4.750 1.1467 0.02579 0.01620 -0.0919 0.4695 1.0000
5.000 1.1542 0.02662 0.01721 -0.0886 0.4626 1.0000
5.250 1.1751 0.02713 0.01773 -0.0876 0.4566 1.0000
5.500 1.2017 0.02764 0.01819 -0.0876 0.4517 1.0000
5.750 1.2067 0.02857 0.01934 -0.0840 0.4451 1.0000
6.000 1.2294 0.02905 0.01982 -0.0834 0.4396 1.0000
6.250 1.2525 0.02965 0.02041 -0.0829 0.4348 1.0000
6.500 1.2561 0.03070 0.02167 -0.0792 0.4287 1.0000
6.750 1.2790 0.03117 0.02217 -0.0786 0.4234 1.0000
7.000 1.3028 0.03178 0.02278 -0.0783 0.4187 1.0000
7.250 1.3011 0.03306 0.02429 -0.0739 0.4130 1.0000
7.500 1.3212 0.03365 0.02492 -0.0730 0.4079 1.0000
7.750 1.3524 0.03403 0.02529 -0.0738 0.4033 1.0000
8.000 1.3395 0.03569 0.02722 -0.0679 0.3977 1.0000
8.250 1.3557 0.03640 0.02801 -0.0664 0.3926 1.0000
8.500 1.3991 0.03639 0.02791 -0.0691 0.3879 1.0000
8.750 1.3698 0.03858 0.03042 -0.0610 0.3825 1.0000
9.000 1.3868 0.03904 0.03096 -0.0596 0.3766 1.0000
9.250 1.4139 0.03889 0.03080 -0.0595 0.3695 1.0000
9.500 1.4016 0.04025 0.03232 -0.0539 0.3634 1.0000
9.750 1.4470 0.03877 0.03073 -0.0560 0.3537 1.0000
10.000 1.4285 0.04024 0.03238 -0.0495 0.3483 1.0000
10.250 1.2087 0.05794 0.05055 -0.0295 0.3522 1.0000
10.500 1.2396 0.05679 0.04948 -0.0290 0.3458 1.0000
10.750 1.1670 0.06738 0.06012 -0.0266 0.3397 1.0000
11.000 1.2615 0.05793 0.05075 -0.0263 0.3318 1.0000
11.250 1.2054 0.06677 0.05967 -0.0246 0.3266 1.0000
11.500 1.4893 0.04171 0.03415 -0.0361 0.3059 1.0000
11.750 1.4732 0.04347 0.03608 -0.0317 0.3001 1.0000
12.000 1.4962 0.04275 0.03532 -0.0309 0.2913 1.0000
12.250 1.4707 0.04545 0.03825 -0.0265 0.2862 1.0000
12.500 1.4964 0.04443 0.03716 -0.0260 0.2771 1.0000
12.750 1.4650 0.04806 0.04108 -0.0221 0.2726 1.0000
13.000 1.4850 0.04724 0.04017 -0.0212 0.2628 1.0000
13.250 1.4488 0.05188 0.04511 -0.0182 0.2584 1.0000
13.500 1.4494 0.05299 0.04625 -0.0169 0.2494 1.0000
13.750 1.4216 0.05768 0.05115 -0.0156 0.2442 1.0000
14.000 1.4042 0.06142 0.05500 -0.0150 0.2363 1.0000
14.250 1.3834 0.06612 0.05985 -0.0150 0.2300 1.0000
14.500 1.3400 0.07458 0.06850 -0.0159 0.2268 1.0000
14.750 1.3350 0.07752 0.07147 -0.0164 0.2162 1.0000
15.000 1.2791 0.08898 0.08310 -0.0186 0.2156 1.0000
15.500 1.2078 0.10662 0.10087 -0.0231 0.2036 1.0000
15.750 0.9395 0.16881 0.16251 -0.0466 0.2008 1.0000
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Polar data table (+)
Polar graphs
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