Dayton-Wright T-1 (daytonwrightt1-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: Dayton-Wright T-1 (daytonwrightt1-il) Reynolds number: 100,000 Max Cl/Cd: 51.15 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-daytonwrightt1-il-100000.txt Download as CSV file: xf-daytonwrightt1-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: Dayton-Wright T-1
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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3805 0.10727 0.10261 -0.0243 1.0000 0.1393
-10.000 -0.4292 0.10748 0.10296 -0.0232 1.0000 0.1410
-9.750 -0.4792 0.10693 0.10252 -0.0238 1.0000 0.1415
-9.500 -0.4774 0.10284 0.09849 -0.0213 1.0000 0.1425
-9.250 -0.4576 0.09992 0.09558 -0.0165 1.0000 0.1442
-9.000 -0.4557 0.09786 0.09356 -0.0138 1.0000 0.1461
-8.750 -0.4622 0.09592 0.09166 -0.0120 1.0000 0.1484
-8.500 -0.4647 0.09278 0.08853 -0.0158 0.9969 0.1541
-8.250 -0.4523 0.08683 0.08251 -0.0254 0.9888 0.1599
-8.000 -0.4246 0.08405 0.07972 -0.0260 0.9838 0.1643
-7.750 -0.4113 0.07819 0.07367 -0.0380 0.9731 0.1751
-7.500 -0.3819 0.07501 0.07051 -0.0387 0.9688 0.1779
-7.250 -0.3876 0.04375 0.03677 -0.0595 0.9608 0.0989
-7.000 -0.3532 0.04073 0.03360 -0.0624 0.9560 0.1008
-6.750 -0.3262 0.03897 0.03167 -0.0631 0.9485 0.1026
-6.500 -0.2908 0.03641 0.02863 -0.0654 0.9427 0.1038
-6.250 -0.2543 0.03449 0.02629 -0.0674 0.9373 0.1062
-6.000 -0.2243 0.03302 0.02438 -0.0680 0.9294 0.1097
-5.750 -0.1817 0.03174 0.02290 -0.0709 0.9246 0.1160
-5.500 -0.1555 0.03108 0.02211 -0.0708 0.9157 0.1224
-5.250 -0.1153 0.03002 0.02094 -0.0730 0.9100 0.1320
-5.000 -0.0833 0.02945 0.02032 -0.0738 0.9025 0.1461
-4.750 -0.0492 0.02893 0.01984 -0.0750 0.8949 0.1650
-4.500 -0.0029 0.02844 0.01932 -0.0781 0.8906 0.1919
-4.250 0.0164 0.02838 0.01935 -0.0768 0.8792 0.2101
-4.000 0.0612 0.02816 0.01914 -0.0796 0.8745 0.2404
-3.750 0.0815 0.02813 0.01920 -0.0784 0.8630 0.2604
-3.500 0.1264 0.02766 0.01881 -0.0810 0.8582 0.2907
-3.250 0.1483 0.02757 0.01877 -0.0799 0.8468 0.3138
-3.000 0.1944 0.02689 0.01818 -0.0826 0.8419 0.3494
-2.750 0.2178 0.02669 0.01805 -0.0816 0.8303 0.3775
-2.500 0.2660 0.02570 0.01721 -0.0844 0.8257 0.4192
-2.250 0.2911 0.02532 0.01698 -0.0837 0.8146 0.4539
-2.000 0.3385 0.02408 0.01603 -0.0862 0.8101 0.5132
-1.750 0.4585 0.02175 0.01497 -0.1018 0.8100 1.0000
-1.500 0.4856 0.02161 0.01464 -0.1012 0.7991 1.0000
-1.250 0.5299 0.02091 0.01375 -0.1032 0.7926 1.0000
-1.000 0.5532 0.02079 0.01353 -0.1018 0.7807 1.0000
-0.750 0.5980 0.02002 0.01261 -0.1039 0.7746 1.0000
-0.500 0.6186 0.01997 0.01248 -0.1021 0.7616 1.0000
-0.250 0.6473 0.01969 0.01211 -0.1016 0.7507 1.0000
0.000 0.6848 0.01913 0.01143 -0.1025 0.7417 1.0000
0.250 0.7074 0.01904 0.01128 -0.1011 0.7281 1.0000
0.500 0.7336 0.01887 0.01103 -0.1002 0.7151 1.0000
0.750 0.7635 0.01860 0.01068 -0.1000 0.7027 1.0000
1.000 0.7961 0.01829 0.01025 -0.1002 0.6902 1.0000
1.250 0.8212 0.01821 0.01009 -0.0992 0.6747 1.0000
1.500 0.8461 0.01818 0.00995 -0.0983 0.6584 1.0000
1.750 0.8713 0.01818 0.00985 -0.0974 0.6413 1.0000
2.000 0.8962 0.01824 0.00978 -0.0964 0.6237 1.0000
2.250 0.9172 0.01843 0.00990 -0.0949 0.6045 1.0000
2.500 0.9386 0.01867 0.01005 -0.0936 0.5853 1.0000
2.750 0.9603 0.01895 0.01022 -0.0923 0.5661 1.0000
3.000 0.9820 0.01927 0.01043 -0.0910 0.5475 1.0000
3.250 1.0037 0.01963 0.01068 -0.0898 0.5295 1.0000
3.500 1.0251 0.02004 0.01098 -0.0887 0.5125 1.0000
3.750 1.0465 0.02048 0.01133 -0.0876 0.4967 1.0000
4.000 1.0685 0.02097 0.01173 -0.0866 0.4825 1.0000
4.250 1.0927 0.02147 0.01213 -0.0861 0.4702 1.0000
4.500 1.1148 0.02202 0.01263 -0.0853 0.4584 1.0000
4.750 1.1358 0.02264 0.01328 -0.0844 0.4477 1.0000
5.000 1.1639 0.02322 0.01371 -0.0847 0.4390 1.0000
5.250 1.1814 0.02389 0.01451 -0.0832 0.4294 1.0000
5.500 1.2092 0.02451 0.01501 -0.0835 0.4218 1.0000
5.750 1.2266 0.02524 0.01591 -0.0821 0.4138 1.0000
6.000 1.2542 0.02591 0.01653 -0.0824 0.4075 1.0000
6.250 1.2730 0.02674 0.01749 -0.0813 0.4008 1.0000
6.500 1.2948 0.02737 0.01816 -0.0807 0.3934 1.0000
6.750 1.3164 0.02805 0.01887 -0.0800 0.3857 1.0000
7.000 1.3345 0.02865 0.01955 -0.0788 0.3775 1.0000
7.250 1.3570 0.02929 0.02018 -0.0783 0.3699 1.0000
7.500 1.3725 0.02999 0.02102 -0.0767 0.3624 1.0000
7.750 1.4045 0.03065 0.02156 -0.0779 0.3563 1.0000
8.000 1.4121 0.03162 0.02285 -0.0751 0.3502 1.0000
8.250 1.4323 0.03233 0.02363 -0.0743 0.3438 1.0000
8.500 1.4555 0.03313 0.02448 -0.0741 0.3376 1.0000
8.750 1.4644 0.03407 0.02565 -0.0716 0.3310 1.0000
9.000 1.4947 0.03463 0.02614 -0.0725 0.3242 1.0000
9.250 1.4983 0.03575 0.02754 -0.0693 0.3177 1.0000
9.500 1.5187 0.03618 0.02799 -0.0686 0.3094 1.0000
9.750 1.5239 0.03705 0.02903 -0.0656 0.3012 1.0000
10.000 1.5500 0.03703 0.02882 -0.0657 0.2903 1.0000
10.250 1.5374 0.03804 0.03016 -0.0600 0.2827 1.0000
10.500 1.5510 0.03813 0.03016 -0.0582 0.2725 1.0000
10.750 1.5398 0.03903 0.03128 -0.0530 0.2645 1.0000
11.000 1.5435 0.03950 0.03173 -0.0501 0.2551 1.0000
11.250 1.5377 0.04034 0.03267 -0.0462 0.2463 1.0000
11.500 1.5315 0.04152 0.03396 -0.0428 0.2379 1.0000
11.750 1.5311 0.04241 0.03487 -0.0402 0.2289 1.0000
12.000 1.5190 0.04435 0.03703 -0.0369 0.2208 1.0000
12.250 1.5212 0.04538 0.03801 -0.0350 0.2120 1.0000
12.500 1.5039 0.04815 0.04107 -0.0322 0.2038 1.0000
12.750 1.4989 0.05004 0.04299 -0.0305 0.1953 1.0000
13.000 1.4848 0.05306 0.04622 -0.0288 0.1865 1.0000
13.250 1.4729 0.05612 0.04940 -0.0276 0.1778 1.0000
13.500 1.4624 0.05920 0.05251 -0.0269 0.1688 1.0000
13.750 1.4450 0.06365 0.05716 -0.0266 0.1593 1.0000
14.000 1.4293 0.06811 0.06168 -0.0267 0.1499 1.0000
14.250 1.4129 0.07288 0.06642 -0.0272 0.1404 1.0000
14.500 1.3934 0.07842 0.07198 -0.0281 0.1309 1.0000
14.750 1.3721 0.08446 0.07805 -0.0292 0.1214 1.0000
15.000 1.3519 0.09041 0.08394 -0.0304 0.1116 1.0000
15.250 1.3337 0.09610 0.08952 -0.0315 0.1016 1.0000
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