Dayton-Wright T-1 (daytonwrightt1-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: Dayton-Wright T-1 (daytonwrightt1-il) Reynolds number: 200,000 Max Cl/Cd: 65.69 at α=2° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-daytonwrightt1-il-200000-n5.txt Download as CSV file: xf-daytonwrightt1-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.3593 0.11063 0.10673 -0.0457 1.0000 0.0367
-13.000 -0.3716 0.10699 0.10313 -0.0454 1.0000 0.0371
-12.500 -0.5854 0.04453 0.03998 -0.1013 0.9726 0.0368
-12.250 -0.5931 0.03869 0.03357 -0.1039 0.9637 0.0370
-12.000 -0.5815 0.03500 0.02938 -0.1055 0.9590 0.0375
-11.750 -0.5678 0.03251 0.02646 -0.1055 0.9536 0.0380
-11.500 -0.5510 0.03058 0.02416 -0.1051 0.9479 0.0384
-11.250 -0.5267 0.02891 0.02236 -0.1056 0.9446 0.0389
-11.000 -0.4992 0.02753 0.02085 -0.1064 0.9422 0.0394
-10.750 -0.4821 0.02652 0.01971 -0.1048 0.9349 0.0398
-10.500 -0.4567 0.02542 0.01847 -0.1048 0.9308 0.0403
-10.250 -0.4289 0.02434 0.01724 -0.1052 0.9277 0.0408
-10.000 -0.4059 0.02343 0.01620 -0.1045 0.9227 0.0414
-9.750 -0.3830 0.02259 0.01521 -0.1037 0.9171 0.0420
-9.500 -0.3559 0.02171 0.01419 -0.1037 0.9133 0.0427
-9.250 -0.3269 0.02090 0.01323 -0.1039 0.9104 0.0435
-9.000 -0.3054 0.02031 0.01252 -0.1026 0.9040 0.0443
-8.750 -0.2801 0.01961 0.01176 -0.1022 0.8990 0.0453
-8.500 -0.2519 0.01896 0.01108 -0.1022 0.8954 0.0463
-8.250 -0.2263 0.01844 0.01051 -0.1017 0.8906 0.0473
-8.000 -0.2023 0.01797 0.00998 -0.1008 0.8845 0.0484
-7.750 -0.1746 0.01745 0.00939 -0.1006 0.8801 0.0498
-7.500 -0.1459 0.01695 0.00880 -0.1005 0.8762 0.0513
-7.250 -0.1232 0.01656 0.00840 -0.0994 0.8692 0.0529
-7.000 -0.0958 0.01615 0.00796 -0.0991 0.8641 0.0554
-6.750 -0.0663 0.01575 0.00750 -0.0992 0.8602 0.0591
-6.500 -0.0430 0.01544 0.00722 -0.0982 0.8526 0.0634
-6.250 -0.0153 0.01510 0.00685 -0.0979 0.8472 0.0698
-6.000 0.0128 0.01477 0.00650 -0.0978 0.8420 0.0784
-5.750 0.0378 0.01451 0.00627 -0.0971 0.8346 0.0876
-5.500 0.0663 0.01423 0.00598 -0.0969 0.8290 0.0979
-5.250 0.0926 0.01402 0.00578 -0.0965 0.8220 0.1084
-5.000 0.1196 0.01382 0.00558 -0.0961 0.8149 0.1203
-4.750 0.1479 0.01360 0.00536 -0.0960 0.8087 0.1332
-4.500 0.1735 0.01343 0.00523 -0.0954 0.8001 0.1472
-4.250 0.2021 0.01320 0.00503 -0.0954 0.7935 0.1671
-4.000 0.2271 0.01304 0.00496 -0.0947 0.7833 0.1877
-3.750 0.2542 0.01286 0.00480 -0.0943 0.7730 0.2084
-3.500 0.2813 0.01270 0.00464 -0.0939 0.7615 0.2279
-3.250 0.3070 0.01259 0.00453 -0.0932 0.7488 0.2459
-3.000 0.3334 0.01250 0.00444 -0.0928 0.7371 0.2644
-2.750 0.3602 0.01241 0.00433 -0.0924 0.7252 0.2832
-2.500 0.3865 0.01235 0.00424 -0.0919 0.7118 0.3012
-2.250 0.4123 0.01230 0.00418 -0.0913 0.6976 0.3188
-2.000 0.4382 0.01226 0.00413 -0.0908 0.6834 0.3373
-1.750 0.4638 0.01222 0.00409 -0.0902 0.6695 0.3571
-1.500 0.4893 0.01219 0.00405 -0.0896 0.6560 0.3785
-1.250 0.5145 0.01216 0.00402 -0.0891 0.6427 0.4015
-1.000 0.5391 0.01212 0.00401 -0.0884 0.6296 0.4273
-0.750 0.5629 0.01202 0.00402 -0.0876 0.6164 0.4660
-0.500 0.5838 0.01114 0.00422 -0.0856 0.6035 0.8408
-0.250 0.6451 0.01132 0.00442 -0.0923 0.5855 0.9541
0.000 0.6856 0.01155 0.00453 -0.0950 0.5687 0.9820
0.250 0.7317 0.01176 0.00461 -0.0991 0.5510 0.9969
0.500 0.7599 0.01195 0.00469 -0.0993 0.5354 1.0000
0.750 0.7803 0.01214 0.00478 -0.0979 0.5203 1.0000
1.000 0.8002 0.01235 0.00489 -0.0964 0.5048 1.0000
1.250 0.8197 0.01257 0.00501 -0.0949 0.4891 1.0000
1.500 0.8388 0.01281 0.00515 -0.0933 0.4731 1.0000
1.750 0.8575 0.01306 0.00531 -0.0916 0.4567 1.0000
2.000 0.8757 0.01333 0.00548 -0.0898 0.4401 1.0000
2.250 0.8934 0.01362 0.00567 -0.0880 0.4239 1.0000
2.500 0.9110 0.01392 0.00587 -0.0862 0.4084 1.0000
3.000 0.9470 0.01453 0.00633 -0.0827 0.3811 1.0000
3.250 0.9654 0.01485 0.00659 -0.0811 0.3696 1.0000
3.500 0.9834 0.01519 0.00687 -0.0795 0.3593 1.0000
3.750 1.0024 0.01551 0.00715 -0.0781 0.3496 1.0000
4.000 1.0209 0.01586 0.00745 -0.0766 0.3413 1.0000
4.250 1.0400 0.01619 0.00777 -0.0752 0.3333 1.0000
4.500 1.0583 0.01657 0.00810 -0.0738 0.3266 1.0000
4.750 1.0774 0.01689 0.00844 -0.0724 0.3200 1.0000
5.000 1.0950 0.01728 0.00880 -0.0709 0.3140 1.0000
5.250 1.1135 0.01766 0.00918 -0.0695 0.3084 1.0000
5.500 1.1320 0.01803 0.00956 -0.0682 0.3019 1.0000
5.750 1.1490 0.01849 0.00997 -0.0667 0.2961 1.0000
6.000 1.1682 0.01886 0.01040 -0.0656 0.2901 1.0000
6.250 1.1864 0.01929 0.01084 -0.0643 0.2842 1.0000
6.500 1.2038 0.01978 0.01131 -0.0630 0.2797 1.0000
6.750 1.2236 0.02019 0.01178 -0.0621 0.2757 1.0000
7.000 1.2428 0.02062 0.01228 -0.0612 0.2712 1.0000
7.250 1.2603 0.02112 0.01279 -0.0600 0.2665 1.0000
7.500 1.2771 0.02168 0.01334 -0.0588 0.2623 1.0000
7.750 1.2958 0.02212 0.01390 -0.0579 0.2573 1.0000
8.000 1.3127 0.02265 0.01449 -0.0568 0.2522 1.0000
8.250 1.3281 0.02327 0.01512 -0.0555 0.2476 1.0000
8.500 1.3450 0.02384 0.01576 -0.0544 0.2428 1.0000
8.750 1.3606 0.02443 0.01644 -0.0533 0.2368 1.0000
9.000 1.3733 0.02519 0.01722 -0.0518 0.2310 1.0000
9.250 1.3885 0.02585 0.01798 -0.0508 0.2244 1.0000
9.500 1.4010 0.02665 0.01883 -0.0494 0.2175 1.0000
9.750 1.4134 0.02749 0.01973 -0.0482 0.2104 1.0000
10.000 1.4251 0.02840 0.02071 -0.0469 0.2022 1.0000
10.250 1.4365 0.02936 0.02175 -0.0457 0.1940 1.0000
10.500 1.4452 0.03052 0.02294 -0.0444 0.1842 1.0000
10.750 1.4546 0.03170 0.02417 -0.0432 0.1711 1.0000
11.000 1.4599 0.03320 0.02566 -0.0418 0.1535 1.0000
11.250 1.4584 0.03530 0.02766 -0.0400 0.1332 1.0000
11.500 1.4544 0.03773 0.03001 -0.0383 0.1182 1.0000
11.750 1.4522 0.04012 0.03239 -0.0369 0.1076 1.0000
12.000 1.4513 0.04252 0.03482 -0.0358 0.0995 1.0000
12.250 1.4483 0.04522 0.03756 -0.0348 0.0929 1.0000
12.500 1.4484 0.04772 0.04013 -0.0340 0.0861 1.0000
12.750 1.4448 0.05071 0.04318 -0.0334 0.0802 1.0000
13.000 1.4426 0.05367 0.04622 -0.0331 0.0735 1.0000
13.250 1.4386 0.05694 0.04957 -0.0329 0.0665 1.0000
13.500 1.4316 0.06068 0.05337 -0.0328 0.0579 1.0000
13.750 1.4210 0.06501 0.05773 -0.0330 0.0486 1.0000
14.000 1.4077 0.06984 0.06259 -0.0335 0.0413 1.0000
14.250 1.3936 0.07492 0.06773 -0.0342 0.0365 1.0000
14.750 1.3664 0.08543 0.07841 -0.0362 0.0309 1.0000
15.000 1.3525 0.09091 0.08399 -0.0375 0.0291 1.0000
|
Polar data table (+)
Polar graphs
<< Back to Dayton-Wright T-1 (daytonwrightt1-il)