Dayton-Wright T-1 (daytonwrightt1-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: Dayton-Wright T-1 (daytonwrightt1-il) Reynolds number: 500,000 Max Cl/Cd: 95.44 at α=1.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-daytonwrightt1-il-500000.txt Download as CSV file: xf-daytonwrightt1-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.3655 0.11162 0.10924 -0.0457 0.9989 0.0437
-13.000 -0.3485 0.10909 0.10671 -0.0472 0.9976 0.0440
-12.750 -0.5960 0.03943 0.03621 -0.1099 0.9774 0.0357
-12.500 -0.5945 0.03364 0.02987 -0.1131 0.9722 0.0358
-12.250 -0.5766 0.03009 0.02591 -0.1151 0.9698 0.0360
-12.000 -0.5630 0.02792 0.02344 -0.1143 0.9635 0.0363
-11.750 -0.5415 0.02600 0.02124 -0.1145 0.9594 0.0366
-11.500 -0.5164 0.02444 0.01942 -0.1148 0.9565 0.0369
-11.250 -0.4940 0.02345 0.01822 -0.1142 0.9520 0.0373
-11.000 -0.4756 0.02197 0.01653 -0.1130 0.9462 0.0377
-10.750 -0.4525 0.02035 0.01477 -0.1126 0.9425 0.0381
-10.500 -0.4268 0.01929 0.01362 -0.1123 0.9395 0.0386
-10.250 -0.4065 0.01856 0.01282 -0.1109 0.9332 0.0390
-10.000 -0.3819 0.01782 0.01201 -0.1102 0.9287 0.0395
-9.750 -0.3560 0.01713 0.01124 -0.1097 0.9251 0.0400
-9.500 -0.3321 0.01654 0.01056 -0.1088 0.9203 0.0406
-9.250 -0.3080 0.01596 0.00991 -0.1079 0.9149 0.0412
-9.000 -0.2821 0.01541 0.00927 -0.1073 0.9106 0.0418
-8.750 -0.2554 0.01494 0.00872 -0.1069 0.9068 0.0426
-8.500 -0.2310 0.01458 0.00829 -0.1060 0.9011 0.0431
-8.250 -0.2067 0.01382 0.00748 -0.1052 0.8959 0.0440
-8.000 -0.1807 0.01328 0.00690 -0.1046 0.8917 0.0450
-7.750 -0.1554 0.01291 0.00652 -0.1039 0.8864 0.0460
-7.500 -0.1295 0.01256 0.00614 -0.1033 0.8808 0.0472
-7.250 -0.1024 0.01222 0.00574 -0.1028 0.8761 0.0486
-7.000 -0.0756 0.01196 0.00542 -0.1023 0.8709 0.0498
-6.750 -0.0503 0.01152 0.00500 -0.1017 0.8648 0.0524
-6.500 -0.0229 0.01126 0.00470 -0.1013 0.8596 0.0555
-6.250 0.0038 0.01096 0.00440 -0.1008 0.8541 0.0600
-6.000 0.0303 0.01068 0.00415 -0.1003 0.8475 0.0677
-5.750 0.0577 0.01038 0.00388 -0.1000 0.8420 0.0825
-5.500 0.0843 0.01018 0.00373 -0.0996 0.8353 0.0970
-5.250 0.1114 0.00999 0.00356 -0.0992 0.8283 0.1092
-5.000 0.1387 0.00982 0.00339 -0.0989 0.8209 0.1208
-4.750 0.1652 0.00965 0.00323 -0.0983 0.8112 0.1329
-4.500 0.1920 0.00950 0.00309 -0.0979 0.8019 0.1464
-4.250 0.2189 0.00936 0.00296 -0.0975 0.7929 0.1618
-4.000 0.2454 0.00922 0.00286 -0.0971 0.7832 0.1791
-3.750 0.2723 0.00909 0.00275 -0.0967 0.7732 0.2003
-3.500 0.2986 0.00899 0.00269 -0.0962 0.7615 0.2240
-3.250 0.3250 0.00889 0.00265 -0.0958 0.7507 0.2475
-2.750 0.3783 0.00880 0.00258 -0.0950 0.7288 0.2914
-2.500 0.4049 0.00877 0.00256 -0.0947 0.7177 0.3089
-2.250 0.4313 0.00876 0.00253 -0.0942 0.7058 0.3254
-2.000 0.4574 0.00875 0.00251 -0.0938 0.6926 0.3424
-1.750 0.4834 0.00875 0.00251 -0.0933 0.6792 0.3596
-1.500 0.5093 0.00876 0.00251 -0.0929 0.6660 0.3769
-1.250 0.5349 0.00877 0.00252 -0.0924 0.6533 0.3968
-1.000 0.5599 0.00876 0.00253 -0.0918 0.6403 0.4230
-0.750 0.5843 0.00867 0.00256 -0.0912 0.6271 0.4682
-0.500 0.5947 0.00762 0.00271 -0.0873 0.6155 0.8774
-0.250 0.6478 0.00782 0.00295 -0.0924 0.6003 0.9598
0.000 0.6884 0.00806 0.00309 -0.0950 0.5855 0.9808
0.750 0.8189 0.00866 0.00338 -0.1057 0.5323 1.0000
1.000 0.8394 0.00883 0.00346 -0.1044 0.5160 1.0000
1.250 0.8595 0.00901 0.00356 -0.1029 0.4992 1.0000
1.500 0.8790 0.00921 0.00366 -0.1014 0.4815 1.0000
1.750 0.8979 0.00943 0.00379 -0.0997 0.4632 1.0000
2.000 0.9163 0.00967 0.00393 -0.0980 0.4445 1.0000
2.250 0.9342 0.00993 0.00409 -0.0961 0.4258 1.0000
2.500 0.9517 0.01020 0.00427 -0.0942 0.4076 1.0000
2.750 0.9692 0.01049 0.00445 -0.0924 0.3906 1.0000
3.000 0.9869 0.01077 0.00465 -0.0905 0.3750 1.0000
3.250 1.0049 0.01105 0.00486 -0.0888 0.3612 1.0000
3.500 1.0228 0.01133 0.00508 -0.0870 0.3494 1.0000
3.750 1.0400 0.01164 0.00532 -0.0851 0.3386 1.0000
4.000 1.0588 0.01191 0.00554 -0.0836 0.3281 1.0000
4.250 1.0774 0.01220 0.00579 -0.0820 0.3188 1.0000
4.500 1.0958 0.01251 0.00605 -0.0805 0.3104 1.0000
4.750 1.1144 0.01279 0.00632 -0.0790 0.3041 1.0000
5.000 1.1333 0.01305 0.00658 -0.0775 0.2979 1.0000
5.250 1.1500 0.01341 0.00689 -0.0758 0.2918 1.0000
5.500 1.1702 0.01366 0.00717 -0.0746 0.2870 1.0000
5.750 1.1900 0.01395 0.00746 -0.0735 0.2821 1.0000
6.000 1.2086 0.01431 0.00781 -0.0722 0.2775 1.0000
6.250 1.2276 0.01468 0.00817 -0.0710 0.2731 1.0000
6.500 1.2487 0.01494 0.00848 -0.0702 0.2688 1.0000
6.750 1.2680 0.01528 0.00883 -0.0691 0.2637 1.0000
7.000 1.2851 0.01576 0.00928 -0.0678 0.2582 1.0000
7.250 1.3067 0.01601 0.00959 -0.0672 0.2536 1.0000
7.500 1.3258 0.01638 0.00997 -0.0662 0.2483 1.0000
7.750 1.3425 0.01690 0.01047 -0.0649 0.2433 1.0000
8.000 1.3632 0.01721 0.01086 -0.0643 0.2391 1.0000
8.250 1.3823 0.01760 0.01129 -0.0635 0.2338 1.0000
8.500 1.3987 0.01815 0.01182 -0.0623 0.2287 1.0000
8.750 1.4178 0.01857 0.01231 -0.0615 0.2240 1.0000
9.000 1.4362 0.01902 0.01280 -0.0607 0.2180 1.0000
9.250 1.4508 0.01969 0.01345 -0.0594 0.2115 1.0000
9.500 1.4699 0.02013 0.01395 -0.0588 0.2038 1.0000
9.750 1.4843 0.02084 0.01466 -0.0576 0.1955 1.0000
10.000 1.4993 0.02154 0.01536 -0.0565 0.1839 1.0000
10.250 1.5120 0.02241 0.01619 -0.0553 0.1688 1.0000
10.500 1.5202 0.02359 0.01727 -0.0536 0.1457 1.0000
10.750 1.5215 0.02529 0.01882 -0.0513 0.1229 1.0000
11.000 1.5233 0.02700 0.02046 -0.0492 0.1085 1.0000
11.250 1.5268 0.02867 0.02210 -0.0474 0.0980 1.0000
11.500 1.5302 0.03039 0.02381 -0.0458 0.0886 1.0000
11.750 1.5319 0.03230 0.02570 -0.0441 0.0786 1.0000
12.000 1.5307 0.03452 0.02787 -0.0424 0.0648 1.0000
12.250 1.5211 0.03759 0.03081 -0.0405 0.0452 1.0000
12.500 1.5101 0.04097 0.03413 -0.0388 0.0335 1.0000
12.750 1.5039 0.04411 0.03731 -0.0377 0.0291 1.0000
13.000 1.5010 0.04703 0.04031 -0.0370 0.0269 1.0000
13.250 1.4955 0.05036 0.04371 -0.0364 0.0253 1.0000
13.500 1.4919 0.05362 0.04707 -0.0361 0.0243 1.0000
13.750 1.4883 0.05698 0.05054 -0.0360 0.0234 1.0000
14.000 1.4823 0.06071 0.05437 -0.0361 0.0227 1.0000
14.250 1.4736 0.06491 0.05867 -0.0363 0.0221 1.0000
14.500 1.4623 0.06956 0.06342 -0.0368 0.0216 1.0000
15.000 1.4391 0.07930 0.07341 -0.0383 0.0208 1.0000
15.250 1.4296 0.08402 0.07825 -0.0392 0.0204 1.0000
15.500 1.4188 0.08903 0.08338 -0.0403 0.0201 1.0000
15.750 1.4071 0.09421 0.08867 -0.0415 0.0198 1.0000
16.000 1.3951 0.09949 0.09406 -0.0429 0.0195 1.0000
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