Dayton-Wright T-1 (daytonwrightt1-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: Dayton-Wright T-1 (daytonwrightt1-il) Reynolds number: 50,000 Max Cl/Cd: 33.39 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-daytonwrightt1-il-50000-n5.txt Download as CSV file: xf-daytonwrightt1-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.3625 0.10569 0.09849 -0.0381 1.0000 0.0857
-10.750 -0.3744 0.10319 0.09607 -0.0370 1.0000 0.0855
-10.500 -0.3883 0.10070 0.09368 -0.0358 1.0000 0.0852
-10.250 -0.4049 0.09822 0.09129 -0.0343 1.0000 0.0849
-10.000 -0.4256 0.09575 0.08892 -0.0327 1.0000 0.0843
-9.750 -0.4479 0.09298 0.08624 -0.0315 1.0000 0.0837
-9.500 -0.4661 0.08940 0.08273 -0.0314 1.0000 0.0831
-9.250 -0.4735 0.08406 0.07737 -0.0348 0.9969 0.0824
-9.000 -0.4693 0.07543 0.06856 -0.0435 0.9886 0.0813
-8.750 -0.4635 0.06627 0.05906 -0.0513 0.9811 0.0807
-8.500 -0.4519 0.06002 0.05246 -0.0556 0.9738 0.0809
-8.250 -0.4333 0.05584 0.04798 -0.0584 0.9675 0.0820
-8.000 -0.4125 0.05246 0.04430 -0.0605 0.9608 0.0841
-7.750 -0.3899 0.04848 0.03983 -0.0631 0.9549 0.0866
-7.500 -0.3689 0.04463 0.03535 -0.0645 0.9480 0.0889
-7.250 -0.3392 0.04108 0.03103 -0.0668 0.9431 0.0911
-7.000 -0.3149 0.03975 0.02962 -0.0669 0.9360 0.0932
-6.750 -0.2845 0.03848 0.02817 -0.0680 0.9300 0.0970
-6.500 -0.2514 0.03685 0.02605 -0.0696 0.9249 0.1031
-6.250 -0.2267 0.03592 0.02505 -0.0695 0.9170 0.1077
-6.000 -0.1918 0.03483 0.02375 -0.0711 0.9117 0.1147
-5.750 -0.1648 0.03406 0.02286 -0.0712 0.9043 0.1227
-5.500 -0.1329 0.03331 0.02191 -0.0721 0.8976 0.1347
-5.250 -0.0965 0.03274 0.02126 -0.0738 0.8925 0.1500
-5.000 -0.0729 0.03243 0.02088 -0.0732 0.8832 0.1652
-4.750 -0.0360 0.03207 0.02062 -0.0750 0.8779 0.1851
-4.500 -0.0126 0.03191 0.02046 -0.0743 0.8685 0.2028
-4.250 0.0233 0.03160 0.02013 -0.0757 0.8625 0.2247
-4.000 0.0494 0.03145 0.01993 -0.0754 0.8537 0.2443
-3.750 0.0840 0.03120 0.01964 -0.0765 0.8469 0.2686
-3.500 0.1119 0.03106 0.01952 -0.0765 0.8385 0.2913
-3.250 0.1442 0.03086 0.01926 -0.0772 0.8309 0.3190
-3.000 0.1734 0.03066 0.01912 -0.0773 0.8227 0.3460
-2.750 0.2038 0.03040 0.01890 -0.0776 0.8144 0.3764
-2.500 0.2332 0.03011 0.01867 -0.0778 0.8061 0.4089
-2.250 0.2632 0.02967 0.01837 -0.0779 0.7975 0.4455
-2.000 0.2892 0.02921 0.01814 -0.0774 0.7880 0.4905
-1.750 0.3638 0.02752 0.01787 -0.0848 0.7823 1.0000
-1.500 0.3931 0.02748 0.01755 -0.0847 0.7720 1.0000
-1.250 0.4267 0.02727 0.01711 -0.0851 0.7627 1.0000
-1.000 0.4482 0.02736 0.01704 -0.0838 0.7500 1.0000
-0.750 0.4779 0.02722 0.01672 -0.0836 0.7398 1.0000
-0.500 0.5084 0.02702 0.01637 -0.0834 0.7296 1.0000
-0.250 0.5297 0.02710 0.01634 -0.0820 0.7165 1.0000
0.000 0.5563 0.02701 0.01614 -0.0813 0.7050 1.0000
0.250 0.5905 0.02665 0.01565 -0.0817 0.6953 1.0000
0.750 0.6353 0.02675 0.01560 -0.0791 0.6682 1.0000
1.000 0.6624 0.02666 0.01542 -0.0785 0.6556 1.0000
1.250 0.6951 0.02637 0.01502 -0.0786 0.6443 1.0000
1.500 0.7183 0.02645 0.01503 -0.0775 0.6298 1.0000
1.750 0.7412 0.02657 0.01510 -0.0764 0.6151 1.0000
2.000 0.7648 0.02668 0.01515 -0.0754 0.6003 1.0000
2.250 0.7889 0.02681 0.01521 -0.0745 0.5855 1.0000
2.500 0.8133 0.02696 0.01530 -0.0736 0.5709 1.0000
2.750 0.8379 0.02714 0.01540 -0.0729 0.5562 1.0000
3.000 0.8628 0.02733 0.01551 -0.0722 0.5419 1.0000
3.250 0.8866 0.02760 0.01572 -0.0714 0.5276 1.0000
3.500 0.9066 0.02804 0.01613 -0.0701 0.5128 1.0000
3.750 0.9269 0.02850 0.01657 -0.0690 0.4986 1.0000
4.000 0.9480 0.02897 0.01701 -0.0680 0.4853 1.0000
4.250 0.9713 0.02940 0.01738 -0.0673 0.4732 1.0000
4.500 0.9945 0.02987 0.01781 -0.0667 0.4618 1.0000
4.750 1.0132 0.03057 0.01855 -0.0655 0.4505 1.0000
5.000 1.0379 0.03108 0.01903 -0.0652 0.4409 1.0000
5.250 1.0577 0.03177 0.01976 -0.0643 0.4309 1.0000
5.500 1.0788 0.03247 0.02048 -0.0636 0.4219 1.0000
5.750 1.1010 0.03313 0.02117 -0.0630 0.4135 1.0000
6.000 1.1212 0.03394 0.02204 -0.0623 0.4058 1.0000
6.250 1.1413 0.03479 0.02296 -0.0616 0.3986 1.0000
6.500 1.1675 0.03545 0.02365 -0.0616 0.3925 1.0000
6.750 1.1795 0.03663 0.02500 -0.0599 0.3853 1.0000
7.000 1.2047 0.03731 0.02571 -0.0599 0.3792 1.0000
7.250 1.2187 0.03849 0.02702 -0.0586 0.3731 1.0000
7.500 1.2320 0.03970 0.02840 -0.0571 0.3673 1.0000
7.750 1.2598 0.04040 0.02915 -0.0575 0.3621 1.0000
8.000 1.2638 0.04194 0.03089 -0.0550 0.3564 1.0000
8.250 1.2722 0.04322 0.03230 -0.0530 0.3499 1.0000
8.500 1.2946 0.04380 0.03292 -0.0525 0.3428 1.0000
8.750 1.2860 0.04571 0.03504 -0.0487 0.3354 1.0000
9.000 1.3142 0.04579 0.03508 -0.0487 0.3273 1.0000
9.250 1.2958 0.04839 0.03794 -0.0444 0.3205 1.0000
9.500 1.3201 0.04867 0.03823 -0.0440 0.3131 1.0000
9.750 1.3068 0.05136 0.04115 -0.0408 0.3073 1.0000
10.000 1.3008 0.05374 0.04372 -0.0385 0.3009 1.0000
10.250 1.3310 0.05366 0.04366 -0.0385 0.2946 1.0000
10.500 1.2855 0.05929 0.04960 -0.0346 0.2891 1.0000
10.750 1.2870 0.06140 0.05184 -0.0334 0.2827 1.0000
11.000 1.2908 0.06339 0.05395 -0.0323 0.2767 1.0000
11.250 1.1879 0.07774 0.06853 -0.0317 0.2688 1.0000
11.500 1.2622 0.07123 0.06209 -0.0302 0.2638 1.0000
11.750 1.1108 0.09539 0.08634 -0.0347 0.2501 1.0000
12.000 1.1623 0.09021 0.08131 -0.0321 0.2474 1.0000
12.500 1.1167 0.10398 0.09522 -0.0351 0.2297 1.0000
12.750 1.0631 0.11735 0.10860 -0.0396 0.2158 1.0000
|
Polar data table (+)
Polar graphs
<< Back to Dayton-Wright T-1 (daytonwrightt1-il)