Dayton-Wright T-1 (daytonwrightt1-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: Dayton-Wright T-1 (daytonwrightt1-il) Reynolds number: 500,000 Max Cl/Cd: 84.45 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-daytonwrightt1-il-500000-n5.txt Download as CSV file: xf-daytonwrightt1-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.500 -0.7493 0.05931 0.05621 -0.0860 1.0000 0.0262
-15.250 -0.8146 0.03916 0.03555 -0.1115 0.9920 0.0260
-15.000 -0.8123 0.03535 0.03148 -0.1148 0.9849 0.0262
-14.750 -0.8030 0.03282 0.02874 -0.1159 0.9788 0.0264
-14.500 -0.7888 0.03080 0.02653 -0.1165 0.9734 0.0266
-14.250 -0.7711 0.02912 0.02467 -0.1169 0.9692 0.0269
-14.000 -0.7554 0.02775 0.02312 -0.1163 0.9628 0.0272
-13.750 -0.7356 0.02643 0.02163 -0.1162 0.9586 0.0275
-13.500 -0.7174 0.02528 0.02031 -0.1154 0.9531 0.0276
-13.250 -0.6983 0.02424 0.01912 -0.1146 0.9474 0.0278
-13.000 -0.6767 0.02328 0.01800 -0.1140 0.9432 0.0280
-12.750 -0.6571 0.02235 0.01694 -0.1130 0.9378 0.0281
-12.500 -0.6384 0.02122 0.01570 -0.1119 0.9320 0.0284
-12.250 -0.6167 0.02033 0.01471 -0.1111 0.9275 0.0287
-12.000 -0.5951 0.01960 0.01391 -0.1102 0.9221 0.0290
-11.750 -0.5727 0.01894 0.01317 -0.1093 0.9162 0.0292
-11.500 -0.5490 0.01834 0.01248 -0.1086 0.9111 0.0296
-11.250 -0.5254 0.01780 0.01187 -0.1078 0.9055 0.0299
-11.000 -0.5015 0.01727 0.01127 -0.1070 0.8999 0.0303
-10.750 -0.4769 0.01674 0.01065 -0.1063 0.8952 0.0307
-10.500 -0.4524 0.01624 0.01006 -0.1056 0.8903 0.0310
-10.250 -0.4278 0.01576 0.00951 -0.1050 0.8849 0.0313
-10.000 -0.4025 0.01530 0.00897 -0.1043 0.8800 0.0316
-9.750 -0.3770 0.01487 0.00845 -0.1038 0.8754 0.0320
-9.500 -0.3516 0.01447 0.00799 -0.1031 0.8699 0.0323
-9.250 -0.3257 0.01410 0.00754 -0.1026 0.8648 0.0326
-8.750 -0.2742 0.01330 0.00663 -0.1015 0.8547 0.0334
-8.500 -0.2482 0.01292 0.00621 -0.1010 0.8493 0.0340
-8.250 -0.2216 0.01260 0.00583 -0.1006 0.8443 0.0346
-8.000 -0.1951 0.01231 0.00551 -0.1001 0.8389 0.0353
-7.750 -0.1684 0.01205 0.00521 -0.0997 0.8330 0.0361
-7.500 -0.1412 0.01181 0.00491 -0.0994 0.8278 0.0370
-7.250 -0.1143 0.01159 0.00465 -0.0990 0.8219 0.0378
-7.000 -0.0872 0.01136 0.00438 -0.0986 0.8157 0.0387
-6.750 -0.0601 0.01112 0.00410 -0.0983 0.8101 0.0401
-6.500 -0.0331 0.01090 0.00388 -0.0979 0.8034 0.0418
-6.250 -0.0058 0.01072 0.00366 -0.0976 0.7968 0.0440
-6.000 0.0213 0.01052 0.00346 -0.0973 0.7901 0.0477
-5.750 0.0483 0.01033 0.00328 -0.0969 0.7826 0.0540
-5.500 0.0754 0.01016 0.00312 -0.0966 0.7753 0.0642
-5.250 0.1024 0.01000 0.00299 -0.0963 0.7666 0.0749
-5.000 0.1292 0.00988 0.00285 -0.0959 0.7559 0.0843
-4.750 0.1557 0.00979 0.00272 -0.0954 0.7421 0.0927
-4.500 0.1819 0.00970 0.00260 -0.0949 0.7271 0.1018
-4.250 0.2084 0.00962 0.00251 -0.0945 0.7132 0.1109
-4.000 0.2346 0.00957 0.00243 -0.0940 0.6982 0.1210
-3.750 0.2602 0.00953 0.00235 -0.0934 0.6805 0.1343
-3.500 0.2856 0.00951 0.00230 -0.0928 0.6625 0.1506
-3.250 0.3112 0.00948 0.00226 -0.0923 0.6467 0.1676
-3.000 0.3371 0.00944 0.00224 -0.0918 0.6334 0.1873
-2.750 0.3629 0.00941 0.00224 -0.0914 0.6214 0.2099
-2.500 0.3887 0.00942 0.00225 -0.0909 0.6087 0.2308
-2.250 0.4143 0.00945 0.00226 -0.0904 0.5952 0.2486
-2.000 0.4402 0.00948 0.00228 -0.0900 0.5812 0.2639
-1.750 0.4660 0.00953 0.00232 -0.0895 0.5679 0.2792
-1.500 0.4917 0.00958 0.00236 -0.0891 0.5554 0.2949
-1.250 0.5172 0.00964 0.00240 -0.0886 0.5424 0.3091
-1.000 0.5428 0.00971 0.00245 -0.0882 0.5289 0.3238
-0.750 0.5681 0.00977 0.00252 -0.0877 0.5151 0.3431
-0.500 0.5932 0.00984 0.00259 -0.0872 0.5009 0.3626
-0.250 0.6181 0.00993 0.00266 -0.0867 0.4863 0.3804
0.000 0.6427 0.01003 0.00275 -0.0861 0.4706 0.3994
0.250 0.6668 0.01013 0.00284 -0.0855 0.4538 0.4241
0.500 0.6901 0.01018 0.00294 -0.0848 0.4359 0.4669
0.750 0.7007 0.00930 0.00314 -0.0812 0.4209 0.8611
1.000 0.7406 0.00952 0.00343 -0.0837 0.4009 0.9458
1.250 0.7804 0.00983 0.00364 -0.0866 0.3826 0.9742
1.500 0.8150 0.01012 0.00383 -0.0883 0.3667 0.9865
1.750 0.8500 0.01040 0.00402 -0.0902 0.3523 0.9944
2.000 0.8863 0.01068 0.00421 -0.0924 0.3394 0.9993
2.500 0.9285 0.01110 0.00453 -0.0901 0.3206 1.0000
2.750 0.9474 0.01133 0.00470 -0.0885 0.3125 1.0000
3.000 0.9674 0.01151 0.00486 -0.0872 0.3057 1.0000
3.250 0.9867 0.01173 0.00504 -0.0856 0.2988 1.0000
3.500 1.0061 0.01194 0.00523 -0.0842 0.2931 1.0000
3.750 1.0261 0.01215 0.00542 -0.0829 0.2866 1.0000
4.250 1.0650 0.01264 0.00585 -0.0801 0.2724 1.0000
4.500 1.0837 0.01290 0.00608 -0.0786 0.2662 1.0000
4.750 1.1020 0.01316 0.00633 -0.0770 0.2620 1.0000
5.000 1.1221 0.01337 0.00656 -0.0758 0.2580 1.0000
5.250 1.1417 0.01362 0.00682 -0.0746 0.2534 1.0000
5.500 1.1609 0.01392 0.00710 -0.0733 0.2493 1.0000
5.750 1.1802 0.01423 0.00741 -0.0721 0.2455 1.0000
6.000 1.2011 0.01449 0.00770 -0.0712 0.2421 1.0000
6.250 1.2213 0.01479 0.00802 -0.0703 0.2379 1.0000
6.500 1.2403 0.01515 0.00838 -0.0692 0.2334 1.0000
6.750 1.2593 0.01553 0.00876 -0.0681 0.2291 1.0000
7.000 1.2798 0.01584 0.00910 -0.0673 0.2241 1.0000
7.250 1.2982 0.01626 0.00951 -0.0662 0.2179 1.0000
7.500 1.3165 0.01669 0.00995 -0.0652 0.2128 1.0000
7.750 1.3363 0.01706 0.01036 -0.0644 0.2079 1.0000
8.000 1.3539 0.01755 0.01085 -0.0633 0.2015 1.0000
8.250 1.3719 0.01803 0.01134 -0.0624 0.1949 1.0000
8.500 1.3891 0.01856 0.01187 -0.0613 0.1869 1.0000
8.750 1.4060 0.01912 0.01244 -0.0603 0.1788 1.0000
9.000 1.4206 0.01983 0.01311 -0.0590 0.1648 1.0000
9.250 1.4286 0.02096 0.01408 -0.0570 0.1383 1.0000
9.500 1.4337 0.02232 0.01530 -0.0548 0.1168 1.0000
9.750 1.4407 0.02360 0.01652 -0.0529 0.1036 1.0000
10.250 1.4580 0.02603 0.01893 -0.0497 0.0861 1.0000
10.500 1.4659 0.02734 0.02023 -0.0482 0.0787 1.0000
10.750 1.4725 0.02878 0.02166 -0.0467 0.0709 1.0000
11.000 1.4795 0.03023 0.02311 -0.0454 0.0622 1.0000
11.250 1.4823 0.03205 0.02489 -0.0438 0.0503 1.0000
11.500 1.4787 0.03446 0.02723 -0.0420 0.0359 1.0000
11.750 1.4754 0.03698 0.02973 -0.0404 0.0270 1.0000
12.000 1.4753 0.03932 0.03210 -0.0392 0.0227 1.0000
12.250 1.4762 0.04167 0.03451 -0.0383 0.0202 1.0000
12.500 1.4785 0.04398 0.03689 -0.0376 0.0188 1.0000
12.750 1.4795 0.04649 0.03947 -0.0370 0.0176 1.0000
13.000 1.4792 0.04923 0.04230 -0.0366 0.0167 1.0000
13.250 1.4800 0.05194 0.04510 -0.0364 0.0160 1.0000
13.500 1.4797 0.05485 0.04810 -0.0362 0.0155 1.0000
13.750 1.4780 0.05802 0.05136 -0.0362 0.0150 1.0000
14.000 1.4747 0.06143 0.05487 -0.0364 0.0145 1.0000
14.250 1.4698 0.06514 0.05868 -0.0366 0.0141 1.0000
14.500 1.4632 0.06917 0.06282 -0.0371 0.0138 1.0000
14.750 1.4547 0.07354 0.06730 -0.0377 0.0135 1.0000
15.000 1.4470 0.07788 0.07174 -0.0384 0.0133 1.0000
15.250 1.4395 0.08228 0.07626 -0.0392 0.0131 1.0000
15.500 1.4308 0.08693 0.08103 -0.0402 0.0130 1.0000
15.750 1.4209 0.09181 0.08603 -0.0414 0.0128 1.0000
16.000 1.4103 0.09685 0.09119 -0.0427 0.0126 1.0000
16.250 1.3995 0.10200 0.09645 -0.0441 0.0124 1.0000
16.500 1.3888 0.10721 0.10177 -0.0456 0.0123 1.0000
|
Polar data table (+)
Polar graphs
<< Back to Dayton-Wright T-1 (daytonwrightt1-il)