Dayton-Wright T-1 (daytonwrightt1-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: Dayton-Wright T-1 (daytonwrightt1-il) Reynolds number: 200,000 Max Cl/Cd: 71.42 at α=2° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-daytonwrightt1-il-200000.txt Download as CSV file: xf-daytonwrightt1-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3469 0.08884 0.08542 -0.0520 0.9839 0.0884
-10.000 -0.3208 0.08634 0.08291 -0.0535 0.9820 0.0902
-9.750 -0.4273 0.04945 0.04514 -0.0857 0.9576 0.0667
-9.500 -0.4052 0.04426 0.03968 -0.0889 0.9548 0.0641
-9.250 -0.4057 0.03949 0.03450 -0.0875 0.9453 0.0628
-9.000 -0.3872 0.03400 0.02832 -0.0892 0.9415 0.0619
-8.750 -0.3661 0.03134 0.02522 -0.0892 0.9364 0.0626
-8.500 -0.3453 0.02932 0.02282 -0.0885 0.9300 0.0634
-8.250 -0.3127 0.02731 0.02039 -0.0898 0.9269 0.0642
-8.000 -0.2753 0.02567 0.01838 -0.0918 0.9248 0.0651
-7.750 -0.2543 0.02482 0.01727 -0.0904 0.9176 0.0658
-7.500 -0.2227 0.02327 0.01567 -0.0913 0.9135 0.0675
-7.250 -0.1837 0.02242 0.01480 -0.0933 0.9110 0.0700
-7.000 -0.1426 0.02160 0.01386 -0.0957 0.9091 0.0733
-6.750 -0.1021 0.02056 0.01269 -0.0978 0.9074 0.0765
-6.500 -0.0854 0.02007 0.01226 -0.0956 0.8979 0.0793
-6.250 -0.0488 0.01938 0.01152 -0.0969 0.8946 0.0849
-6.000 -0.0112 0.01853 0.01074 -0.0985 0.8922 0.0935
-5.750 0.0129 0.01808 0.01032 -0.0976 0.8850 0.1048
-5.500 0.0435 0.01754 0.00983 -0.0978 0.8796 0.1221
-5.250 0.0793 0.01702 0.00930 -0.0989 0.8763 0.1411
-5.000 0.1088 0.01667 0.00898 -0.0989 0.8707 0.1577
-4.750 0.1350 0.01636 0.00872 -0.0983 0.8632 0.1740
-4.500 0.1692 0.01584 0.00830 -0.0991 0.8593 0.1938
-4.250 0.1946 0.01563 0.00817 -0.0984 0.8514 0.2150
-4.000 0.2251 0.01532 0.00787 -0.0984 0.8448 0.2413
-3.750 0.2575 0.01486 0.00750 -0.0988 0.8390 0.2670
-3.500 0.2825 0.01461 0.00728 -0.0978 0.8287 0.2906
-3.250 0.3136 0.01423 0.00692 -0.0979 0.8219 0.3149
-3.000 0.3387 0.01402 0.00676 -0.0970 0.8118 0.3371
-2.750 0.3676 0.01375 0.00649 -0.0968 0.8036 0.3608
-2.500 0.3945 0.01347 0.00624 -0.0962 0.7937 0.3833
-2.250 0.4203 0.01321 0.00605 -0.0955 0.7834 0.4069
-2.000 0.4491 0.01286 0.00574 -0.0953 0.7746 0.4353
-1.750 0.4722 0.01257 0.00561 -0.0942 0.7629 0.4700
-1.500 0.4943 0.01195 0.00540 -0.0929 0.7531 0.5568
-1.250 0.6035 0.01128 0.00560 -0.1081 0.7425 0.9919
-1.000 0.6484 0.01126 0.00546 -0.1116 0.7298 1.0000
-0.750 0.6724 0.01128 0.00537 -0.1107 0.7173 1.0000
-0.500 0.6966 0.01131 0.00526 -0.1099 0.7045 1.0000
-0.250 0.7204 0.01135 0.00518 -0.1089 0.6910 1.0000
0.000 0.7427 0.01143 0.00517 -0.1078 0.6761 1.0000
0.250 0.7650 0.01153 0.00518 -0.1066 0.6613 1.0000
0.500 0.7872 0.01164 0.00520 -0.1054 0.6464 1.0000
0.750 0.8091 0.01178 0.00524 -0.1042 0.6312 1.0000
1.000 0.8306 0.01194 0.00531 -0.1030 0.6156 1.0000
1.250 0.8517 0.01212 0.00538 -0.1016 0.5995 1.0000
1.500 0.8722 0.01232 0.00548 -0.1002 0.5828 1.0000
1.750 0.8921 0.01253 0.00561 -0.0986 0.5653 1.0000
2.000 0.9113 0.01276 0.00574 -0.0969 0.5469 1.0000
2.250 0.9298 0.01302 0.00589 -0.0952 0.5278 1.0000
2.500 0.9478 0.01331 0.00606 -0.0933 0.5084 1.0000
2.750 0.9653 0.01363 0.00625 -0.0913 0.4892 1.0000
3.000 0.9825 0.01396 0.00648 -0.0894 0.4701 1.0000
3.250 0.9999 0.01432 0.00674 -0.0875 0.4521 1.0000
3.500 1.0176 0.01471 0.00703 -0.0858 0.4357 1.0000
3.750 1.0357 0.01513 0.00733 -0.0841 0.4210 1.0000
4.000 1.0545 0.01554 0.00765 -0.0826 0.4076 1.0000
4.250 1.0740 0.01594 0.00802 -0.0813 0.3956 1.0000
4.500 1.0944 0.01639 0.00839 -0.0802 0.3856 1.0000
4.750 1.1149 0.01682 0.00877 -0.0792 0.3761 1.0000
5.000 1.1361 0.01726 0.00919 -0.0783 0.3676 1.0000
5.250 1.1572 0.01770 0.00958 -0.0774 0.3597 1.0000
5.500 1.1789 0.01816 0.01002 -0.0766 0.3523 1.0000
5.750 1.1991 0.01856 0.01043 -0.0756 0.3448 1.0000
6.000 1.2220 0.01908 0.01089 -0.0752 0.3382 1.0000
6.250 1.2420 0.01947 0.01136 -0.0741 0.3321 1.0000
6.500 1.2640 0.01993 0.01180 -0.0735 0.3265 1.0000
6.750 1.2863 0.02044 0.01232 -0.0730 0.3208 1.0000
7.000 1.3051 0.02085 0.01281 -0.0719 0.3152 1.0000
7.250 1.3260 0.02131 0.01326 -0.0711 0.3097 1.0000
7.500 1.3477 0.02184 0.01381 -0.0706 0.3046 1.0000
7.750 1.3650 0.02227 0.01437 -0.0692 0.2999 1.0000
8.000 1.3833 0.02272 0.01485 -0.0680 0.2949 1.0000
8.250 1.4043 0.02328 0.01539 -0.0675 0.2893 1.0000
8.500 1.4140 0.02369 0.01596 -0.0648 0.2836 1.0000
8.750 1.4272 0.02414 0.01642 -0.0629 0.2772 1.0000
9.000 1.4397 0.02469 0.01704 -0.0610 0.2709 1.0000
9.250 1.4493 0.02521 0.01767 -0.0587 0.2646 1.0000
9.500 1.4649 0.02582 0.01821 -0.0575 0.2583 1.0000
9.750 1.4711 0.02646 0.01907 -0.0549 0.2521 1.0000
10.000 1.4799 0.02714 0.01980 -0.0528 0.2454 1.0000
10.250 1.4880 0.02794 0.02070 -0.0508 0.2385 1.0000
10.500 1.4938 0.02881 0.02165 -0.0487 0.2307 1.0000
10.750 1.4999 0.02980 0.02274 -0.0467 0.2227 1.0000
11.000 1.5045 0.03093 0.02393 -0.0448 0.2140 1.0000
11.250 1.5104 0.03212 0.02526 -0.0432 0.2047 1.0000
11.500 1.5140 0.03353 0.02671 -0.0416 0.1957 1.0000
11.750 1.5182 0.03503 0.02832 -0.0402 0.1844 1.0000
12.000 1.5212 0.03673 0.03010 -0.0389 0.1711 1.0000
12.250 1.5206 0.03881 0.03220 -0.0375 0.1559 1.0000
12.500 1.5164 0.04135 0.03472 -0.0362 0.1400 1.0000
12.750 1.5086 0.04440 0.03772 -0.0349 0.1262 1.0000
13.000 1.4981 0.04788 0.04118 -0.0338 0.1147 1.0000
13.250 1.4856 0.05180 0.04509 -0.0330 0.1046 1.0000
13.500 1.4733 0.05592 0.04925 -0.0326 0.0941 1.0000
13.750 1.4587 0.06052 0.05389 -0.0324 0.0835 1.0000
14.000 1.4417 0.06564 0.05906 -0.0326 0.0731 1.0000
14.250 1.4239 0.07110 0.06455 -0.0331 0.0638 1.0000
14.500 1.4064 0.07671 0.07021 -0.0339 0.0570 1.0000
14.750 1.3877 0.08266 0.07621 -0.0350 0.0530 1.0000
15.000 1.3727 0.08823 0.08187 -0.0362 0.0494 1.0000
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