Dayton-Wright T-1 (daytonwrightt1-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: Dayton-Wright T-1 (daytonwrightt1-il) Reynolds number: 100,000 Max Cl/Cd: 50.44 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-daytonwrightt1-il-100000-n5.txt Download as CSV file: xf-daytonwrightt1-il-100000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.3807 0.09094 0.08583 -0.0479 0.9924 0.0549
-10.750 -0.3842 0.08432 0.07921 -0.0541 0.9857 0.0544
-10.500 -0.4947 0.05033 0.04438 -0.0832 0.9618 0.0520
-10.250 -0.4819 0.04543 0.03907 -0.0863 0.9570 0.0525
-10.000 -0.4736 0.04241 0.03574 -0.0859 0.9488 0.0529
-9.750 -0.4517 0.03979 0.03282 -0.0872 0.9443 0.0538
-9.500 -0.4316 0.03773 0.03047 -0.0875 0.9390 0.0549
-9.250 -0.4134 0.03564 0.02804 -0.0872 0.9325 0.0562
-9.000 -0.3873 0.03331 0.02527 -0.0882 0.9286 0.0575
-8.750 -0.3604 0.03130 0.02283 -0.0888 0.9248 0.0586
-8.500 -0.3416 0.02988 0.02105 -0.0875 0.9174 0.0595
-8.250 -0.3112 0.02871 0.01982 -0.0884 0.9136 0.0607
-8.000 -0.2768 0.02768 0.01870 -0.0898 0.9109 0.0623
-7.750 -0.2563 0.02696 0.01787 -0.0885 0.9036 0.0639
-7.500 -0.2267 0.02610 0.01682 -0.0889 0.8988 0.0668
-7.250 -0.1930 0.02519 0.01578 -0.0900 0.8955 0.0698
-7.000 -0.1656 0.02457 0.01515 -0.0899 0.8903 0.0728
-6.750 -0.1409 0.02395 0.01444 -0.0893 0.8835 0.0764
-6.500 -0.1084 0.02319 0.01361 -0.0900 0.8797 0.0811
-6.250 -0.0747 0.02255 0.01293 -0.0909 0.8763 0.0883
-6.000 -0.0552 0.02220 0.01259 -0.0893 0.8673 0.0956
-5.750 -0.0226 0.02165 0.01202 -0.0901 0.8631 0.1071
-5.500 0.0073 0.02122 0.01156 -0.0903 0.8580 0.1196
-5.250 0.0314 0.02095 0.01129 -0.0894 0.8501 0.1325
-5.000 0.0646 0.02053 0.01090 -0.0902 0.8458 0.1498
-4.750 0.0895 0.02031 0.01075 -0.0896 0.8383 0.1679
-4.500 0.1181 0.02002 0.01053 -0.0895 0.8318 0.1877
-4.250 0.1523 0.01961 0.01014 -0.0904 0.8277 0.2080
-4.000 0.1738 0.01950 0.01007 -0.0891 0.8180 0.2248
-3.750 0.2062 0.01916 0.00974 -0.0896 0.8126 0.2463
-3.500 0.2312 0.01902 0.00962 -0.0888 0.8039 0.2667
-3.250 0.2615 0.01873 0.00938 -0.0889 0.7970 0.2882
-3.000 0.2882 0.01854 0.00922 -0.0884 0.7879 0.3098
-2.750 0.3188 0.01824 0.00891 -0.0884 0.7795 0.3337
-2.500 0.3443 0.01805 0.00875 -0.0876 0.7682 0.3563
-2.250 0.3765 0.01767 0.00839 -0.0880 0.7597 0.3824
-2.000 0.4017 0.01748 0.00825 -0.0873 0.7477 0.4082
-1.750 0.4279 0.01723 0.00808 -0.0867 0.7364 0.4385
-1.500 0.4564 0.01678 0.00777 -0.0865 0.7265 0.4831
-1.250 0.5212 0.01565 0.00788 -0.0927 0.7138 0.9397
-1.000 0.5865 0.01563 0.00771 -0.1002 0.6996 1.0000
-0.750 0.6102 0.01566 0.00759 -0.0992 0.6861 1.0000
-0.500 0.6343 0.01569 0.00748 -0.0982 0.6727 1.0000
-0.250 0.6585 0.01573 0.00739 -0.0973 0.6591 1.0000
0.000 0.6823 0.01580 0.00732 -0.0964 0.6452 1.0000
0.250 0.7043 0.01593 0.00733 -0.0952 0.6305 1.0000
0.500 0.7264 0.01606 0.00737 -0.0940 0.6158 1.0000
0.750 0.7483 0.01622 0.00742 -0.0928 0.6012 1.0000
1.000 0.7701 0.01639 0.00749 -0.0915 0.5864 1.0000
1.250 0.7915 0.01658 0.00758 -0.0903 0.5710 1.0000
1.500 0.8124 0.01680 0.00769 -0.0889 0.5552 1.0000
1.750 0.8329 0.01703 0.00782 -0.0875 0.5389 1.0000
2.000 0.8531 0.01728 0.00799 -0.0861 0.5226 1.0000
2.250 0.8730 0.01755 0.00817 -0.0846 0.5063 1.0000
2.500 0.8929 0.01785 0.00837 -0.0832 0.4905 1.0000
2.750 0.9125 0.01816 0.00860 -0.0818 0.4749 1.0000
3.000 0.9320 0.01850 0.00885 -0.0804 0.4599 1.0000
3.250 0.9513 0.01886 0.00913 -0.0789 0.4451 1.0000
3.500 0.9704 0.01924 0.00945 -0.0775 0.4308 1.0000
3.750 0.9895 0.01964 0.00979 -0.0762 0.4175 1.0000
4.000 1.0088 0.02006 0.01014 -0.0748 0.4054 1.0000
4.250 1.0281 0.02050 0.01049 -0.0736 0.3945 1.0000
4.500 1.0478 0.02093 0.01093 -0.0724 0.3843 1.0000
4.750 1.0679 0.02140 0.01133 -0.0713 0.3759 1.0000
5.000 1.0880 0.02186 0.01181 -0.0703 0.3675 1.0000
5.250 1.1087 0.02237 0.01225 -0.0694 0.3607 1.0000
5.500 1.1291 0.02285 0.01279 -0.0685 0.3535 1.0000
5.750 1.1498 0.02336 0.01329 -0.0676 0.3472 1.0000
6.000 1.1707 0.02389 0.01383 -0.0669 0.3412 1.0000
6.250 1.1907 0.02442 0.01442 -0.0659 0.3350 1.0000
6.500 1.2120 0.02497 0.01495 -0.0653 0.3299 1.0000
6.750 1.2320 0.02554 0.01557 -0.0644 0.3245 1.0000
7.000 1.2495 0.02610 0.01622 -0.0632 0.3183 1.0000
7.250 1.2688 0.02667 0.01675 -0.0622 0.3124 1.0000
7.500 1.2826 0.02727 0.01747 -0.0604 0.3056 1.0000
7.750 1.2976 0.02787 0.01811 -0.0589 0.2990 1.0000
8.000 1.3143 0.02850 0.01878 -0.0576 0.2933 1.0000
8.250 1.3274 0.02918 0.01961 -0.0559 0.2872 1.0000
8.500 1.3433 0.02984 0.02032 -0.0547 0.2821 1.0000
8.750 1.3610 0.03053 0.02105 -0.0538 0.2777 1.0000
9.000 1.3732 0.03133 0.02206 -0.0521 0.2725 1.0000
9.250 1.3865 0.03210 0.02293 -0.0507 0.2674 1.0000
9.500 1.4028 0.03282 0.02365 -0.0496 0.2627 1.0000
9.750 1.4110 0.03380 0.02486 -0.0477 0.2573 1.0000
10.000 1.4200 0.03474 0.02594 -0.0459 0.2515 1.0000
10.250 1.4307 0.03561 0.02683 -0.0444 0.2458 1.0000
10.500 1.4328 0.03691 0.02837 -0.0422 0.2387 1.0000
10.750 1.4368 0.03807 0.02958 -0.0403 0.2315 1.0000
11.000 1.4371 0.03960 0.03130 -0.0382 0.2233 1.0000
11.250 1.4376 0.04113 0.03288 -0.0364 0.2152 1.0000
11.500 1.4363 0.04303 0.03498 -0.0348 0.2061 1.0000
11.750 1.4345 0.04499 0.03700 -0.0333 0.1977 1.0000
12.000 1.4313 0.04734 0.03953 -0.0320 0.1875 1.0000
12.250 1.4265 0.04995 0.04228 -0.0310 0.1766 1.0000
12.500 1.4202 0.05290 0.04532 -0.0302 0.1650 1.0000
12.750 1.4120 0.05624 0.04873 -0.0297 0.1532 1.0000
13.000 1.4018 0.06002 0.05254 -0.0295 0.1427 1.0000
13.250 1.3906 0.06415 0.05673 -0.0295 0.1336 1.0000
13.500 1.3777 0.06870 0.06134 -0.0299 0.1263 1.0000
13.750 1.3623 0.07377 0.06646 -0.0305 0.1200 1.0000
14.000 1.3470 0.07908 0.07186 -0.0314 0.1145 1.0000
14.250 1.3302 0.08479 0.07766 -0.0327 0.1094 1.0000
14.500 1.3116 0.09088 0.08380 -0.0342 0.1052 1.0000
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