Dayton-Wright T-1 (daytonwrightt1-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: Dayton-Wright T-1 (daytonwrightt1-il) Reynolds number: 1,000,000 Max Cl/Cd: 109.93 at α=2° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-daytonwrightt1-il-1000000.txt Download as CSV file: xf-daytonwrightt1-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.500 -0.3829 0.16447 0.16260 -0.0306 1.0000 0.0212
-17.250 -0.3755 0.16160 0.15973 -0.0319 1.0000 0.0219
-15.750 -0.8818 0.03810 0.03526 -0.1106 0.9974 0.0249
-15.500 -0.8727 0.03493 0.03192 -0.1141 0.9942 0.0251
-15.250 -0.8603 0.03259 0.02942 -0.1156 0.9900 0.0253
-15.000 -0.8414 0.03066 0.02736 -0.1170 0.9869 0.0256
-14.750 -0.8195 0.02890 0.02546 -0.1184 0.9848 0.0258
-14.500 -0.7968 0.02731 0.02373 -0.1195 0.9828 0.0261
-14.250 -0.7785 0.02597 0.02226 -0.1192 0.9780 0.0264
-14.000 -0.7579 0.02476 0.02092 -0.1190 0.9735 0.0266
-13.750 -0.7353 0.02379 0.01982 -0.1189 0.9698 0.0270
-13.500 -0.7166 0.02297 0.01888 -0.1177 0.9639 0.0272
-13.250 -0.6966 0.02216 0.01795 -0.1166 0.9584 0.0274
-13.000 -0.6752 0.02146 0.01713 -0.1157 0.9537 0.0276
-12.750 -0.6546 0.02088 0.01644 -0.1145 0.9475 0.0277
-12.500 -0.6412 0.01891 0.01427 -0.1128 0.9412 0.0281
-12.250 -0.6217 0.01787 0.01315 -0.1115 0.9354 0.0284
-12.000 -0.6000 0.01714 0.01236 -0.1105 0.9296 0.0287
-11.750 -0.5769 0.01654 0.01168 -0.1096 0.9247 0.0290
-11.500 -0.5531 0.01600 0.01110 -0.1088 0.9198 0.0294
-11.250 -0.5287 0.01554 0.01058 -0.1080 0.9146 0.0297
-11.000 -0.5040 0.01508 0.01005 -0.1073 0.9099 0.0301
-10.750 -0.4791 0.01460 0.00950 -0.1067 0.9053 0.0305
-10.500 -0.4542 0.01412 0.00896 -0.1060 0.9003 0.0308
-10.250 -0.4289 0.01368 0.00844 -0.1053 0.8954 0.0311
-10.000 -0.4031 0.01327 0.00796 -0.1047 0.8908 0.0315
-9.750 -0.3773 0.01289 0.00753 -0.1042 0.8861 0.0318
-9.500 -0.3510 0.01256 0.00714 -0.1036 0.8812 0.0321
-9.250 -0.3244 0.01227 0.00678 -0.1032 0.8765 0.0323
-9.000 -0.3001 0.01159 0.00603 -0.1024 0.8717 0.0329
-8.750 -0.2745 0.01115 0.00556 -0.1019 0.8667 0.0335
-8.500 -0.2479 0.01083 0.00520 -0.1014 0.8616 0.0342
-8.250 -0.2207 0.01059 0.00490 -0.1010 0.8568 0.0349
-8.000 -0.1937 0.01032 0.00463 -0.1007 0.8518 0.0355
-7.750 -0.1665 0.01008 0.00434 -0.1003 0.8466 0.0362
-7.500 -0.1391 0.00988 0.00408 -0.1000 0.8414 0.0368
-7.250 -0.1116 0.00968 0.00385 -0.0997 0.8362 0.0373
-7.000 -0.0847 0.00937 0.00351 -0.0992 0.8305 0.0386
-6.750 -0.0574 0.00915 0.00325 -0.0989 0.8249 0.0401
-6.500 -0.0298 0.00896 0.00306 -0.0987 0.8193 0.0416
-6.250 -0.0021 0.00881 0.00287 -0.0984 0.8129 0.0431
-6.000 0.0252 0.00861 0.00266 -0.0980 0.8065 0.0471
-5.750 0.0523 0.00839 0.00248 -0.0977 0.7980 0.0549
-5.500 0.0789 0.00819 0.00232 -0.0973 0.7887 0.0718
-5.250 0.1061 0.00804 0.00221 -0.0970 0.7788 0.0845
-5.000 0.1335 0.00793 0.00210 -0.0967 0.7702 0.0943
-4.750 0.1606 0.00784 0.00200 -0.0963 0.7594 0.1033
-4.250 0.2146 0.00768 0.00184 -0.0957 0.7353 0.1247
-3.750 0.2685 0.00754 0.00172 -0.0951 0.7125 0.1538
-3.500 0.2953 0.00748 0.00168 -0.0947 0.7005 0.1713
-3.000 0.3478 0.00741 0.00163 -0.0939 0.6731 0.2127
-2.750 0.3742 0.00739 0.00163 -0.0935 0.6593 0.2325
-2.500 0.4008 0.00738 0.00164 -0.0932 0.6465 0.2544
-2.250 0.4273 0.00740 0.00166 -0.0929 0.6339 0.2749
-2.000 0.4536 0.00743 0.00168 -0.0925 0.6213 0.2922
-1.750 0.4800 0.00747 0.00171 -0.0922 0.6085 0.3069
-1.500 0.5067 0.00750 0.00173 -0.0919 0.5962 0.3211
-1.250 0.5331 0.00755 0.00177 -0.0916 0.5839 0.3364
-1.000 0.5593 0.00761 0.00181 -0.0913 0.5711 0.3516
-0.750 0.5853 0.00768 0.00186 -0.0909 0.5571 0.3669
-0.500 0.6114 0.00773 0.00191 -0.0906 0.5427 0.3862
-0.250 0.6370 0.00776 0.00197 -0.0902 0.5281 0.4144
0.000 0.6620 0.00775 0.00204 -0.0898 0.5136 0.4586
0.250 0.6739 0.00683 0.00217 -0.0866 0.5006 0.8533
0.500 0.6996 0.00685 0.00235 -0.0859 0.4848 0.9361
0.750 0.7393 0.00709 0.00253 -0.0886 0.4658 0.9703
1.000 0.7741 0.00735 0.00268 -0.0903 0.4463 0.9830
1.250 0.8142 0.00763 0.00285 -0.0932 0.4248 0.9895
1.500 0.8530 0.00792 0.00301 -0.0959 0.4039 0.9944
1.750 0.8927 0.00819 0.00317 -0.0988 0.3832 0.9974
2.000 0.9300 0.00846 0.00333 -0.1013 0.3645 0.9998
2.250 0.9519 0.00867 0.00347 -0.1003 0.3504 1.0000
2.500 0.9710 0.00889 0.00361 -0.0987 0.3379 1.0000
2.750 0.9903 0.00910 0.00376 -0.0971 0.3260 1.0000
3.000 1.0099 0.00929 0.00390 -0.0956 0.3152 1.0000
3.250 1.0288 0.00951 0.00406 -0.0940 0.3046 1.0000
3.500 1.0484 0.00971 0.00422 -0.0926 0.2958 1.0000
3.750 1.0679 0.00991 0.00438 -0.0911 0.2886 1.0000
4.000 1.0883 0.01008 0.00454 -0.0898 0.2823 1.0000
4.250 1.1068 0.01033 0.00473 -0.0882 0.2747 1.0000
4.500 1.1277 0.01048 0.00489 -0.0870 0.2697 1.0000
4.750 1.1478 0.01068 0.00507 -0.0857 0.2647 1.0000
5.000 1.1671 0.01093 0.00529 -0.0843 0.2594 1.0000
5.250 1.1884 0.01110 0.00547 -0.0833 0.2562 1.0000
5.500 1.2086 0.01128 0.00566 -0.0821 0.2519 1.0000
5.750 1.2271 0.01154 0.00589 -0.0806 0.2464 1.0000
6.000 1.2465 0.01178 0.00613 -0.0793 0.2415 1.0000
6.250 1.2678 0.01198 0.00634 -0.0785 0.2378 1.0000
6.500 1.2880 0.01224 0.00659 -0.0774 0.2330 1.0000
6.750 1.3066 0.01258 0.00691 -0.0762 0.2270 1.0000
7.000 1.3288 0.01278 0.00714 -0.0755 0.2237 1.0000
7.250 1.3496 0.01305 0.00742 -0.0747 0.2196 1.0000
7.500 1.3690 0.01339 0.00776 -0.0737 0.2146 1.0000
7.750 1.3892 0.01370 0.00808 -0.0729 0.2103 1.0000
8.000 1.4101 0.01398 0.00838 -0.0722 0.2056 1.0000
8.250 1.4283 0.01441 0.00878 -0.0711 0.1985 1.0000
8.500 1.4482 0.01475 0.00914 -0.0703 0.1919 1.0000
8.750 1.4653 0.01526 0.00960 -0.0692 0.1827 1.0000
9.000 1.4823 0.01577 0.01008 -0.0681 0.1704 1.0000
9.250 1.4925 0.01667 0.01082 -0.0660 0.1449 1.0000
9.500 1.4940 0.01811 0.01204 -0.0629 0.1149 1.0000
9.750 1.5018 0.01921 0.01307 -0.0607 0.1003 1.0000
10.000 1.5117 0.02022 0.01404 -0.0589 0.0906 1.0000
10.250 1.5218 0.02125 0.01503 -0.0573 0.0823 1.0000
10.500 1.5327 0.02224 0.01601 -0.0558 0.0746 1.0000
10.750 1.5405 0.02346 0.01719 -0.0541 0.0642 1.0000
11.000 1.5394 0.02534 0.01893 -0.0515 0.0448 1.0000
11.250 1.5328 0.02769 0.02117 -0.0486 0.0278 1.0000
11.500 1.5350 0.02951 0.02298 -0.0468 0.0226 1.0000
11.750 1.5399 0.03116 0.02467 -0.0454 0.0203 1.0000
12.000 1.5451 0.03284 0.02640 -0.0441 0.0190 1.0000
12.250 1.5479 0.03480 0.02841 -0.0429 0.0178 1.0000
12.500 1.5546 0.03647 0.03015 -0.0420 0.0172 1.0000
12.750 1.5594 0.03837 0.03212 -0.0412 0.0165 1.0000
13.000 1.5623 0.04052 0.03433 -0.0404 0.0159 1.0000
13.250 1.5631 0.04297 0.03685 -0.0396 0.0154 1.0000
13.500 1.5605 0.04587 0.03984 -0.0389 0.0149 1.0000
13.750 1.5619 0.04842 0.04247 -0.0386 0.0146 1.0000
14.000 1.5630 0.05108 0.04521 -0.0383 0.0143 1.0000
14.250 1.5626 0.05399 0.04821 -0.0382 0.0141 1.0000
14.500 1.5606 0.05715 0.05146 -0.0382 0.0138 1.0000
14.750 1.5571 0.06057 0.05496 -0.0383 0.0135 1.0000
15.000 1.5519 0.06427 0.05876 -0.0386 0.0133 1.0000
15.250 1.5449 0.06829 0.06287 -0.0390 0.0131 1.0000
15.500 1.5361 0.07264 0.06732 -0.0395 0.0129 1.0000
15.750 1.5245 0.07744 0.07223 -0.0402 0.0128 1.0000
16.000 1.5111 0.08260 0.07750 -0.0411 0.0126 1.0000
16.250 1.4955 0.08819 0.08320 -0.0423 0.0125 1.0000
16.500 1.4781 0.09414 0.08928 -0.0436 0.0123 1.0000
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Polar data table (+)
Polar graphs
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