Dayton-Wright T-1 (daytonwrightt1-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: Dayton-Wright T-1 (daytonwrightt1-il) Reynolds number: 1,000,000 Max Cl/Cd: 103.44 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-daytonwrightt1-il-1000000-n5.txt Download as CSV file: xf-daytonwrightt1-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.000 -0.7269 0.09561 0.09332 -0.0659 1.0000 0.0220
-17.750 -0.8185 0.07694 0.07441 -0.0787 1.0000 0.0220
-17.500 -0.8888 0.06325 0.06056 -0.0886 1.0000 0.0220
-17.250 -1.0259 0.03814 0.03508 -0.1118 1.0000 0.0217
-17.000 -1.0222 0.03298 0.02968 -0.1178 0.9953 0.0218
-16.750 -1.0130 0.03056 0.02711 -0.1192 0.9901 0.0220
-16.500 -0.9990 0.02882 0.02526 -0.1197 0.9845 0.0221
-16.250 -0.9821 0.02743 0.02376 -0.1198 0.9794 0.0223
-16.000 -0.9645 0.02621 0.02243 -0.1195 0.9737 0.0225
-15.750 -0.9461 0.02510 0.02121 -0.1191 0.9688 0.0227
-15.500 -0.9293 0.02407 0.02007 -0.1182 0.9623 0.0229
-15.250 -0.9106 0.02312 0.01901 -0.1173 0.9569 0.0230
-15.000 -0.8925 0.02228 0.01806 -0.1162 0.9503 0.0232
-14.750 -0.8729 0.02149 0.01717 -0.1152 0.9446 0.0233
-14.500 -0.8522 0.02079 0.01637 -0.1142 0.9395 0.0234
-14.250 -0.8306 0.02019 0.01568 -0.1133 0.9337 0.0236
-14.000 -0.8085 0.01961 0.01500 -0.1124 0.9283 0.0237
-13.750 -0.7861 0.01903 0.01433 -0.1116 0.9234 0.0238
-13.500 -0.7662 0.01814 0.01334 -0.1105 0.9176 0.0240
-13.250 -0.7452 0.01737 0.01248 -0.1095 0.9122 0.0242
-13.000 -0.7226 0.01674 0.01177 -0.1086 0.9073 0.0244
-12.750 -0.6992 0.01619 0.01116 -0.1078 0.9016 0.0247
-12.500 -0.6753 0.01571 0.01059 -0.1071 0.8956 0.0249
-12.250 -0.6508 0.01526 0.01008 -0.1064 0.8899 0.0251
-12.000 -0.6259 0.01484 0.00960 -0.1057 0.8840 0.0253
-11.750 -0.6008 0.01444 0.00913 -0.1050 0.8787 0.0255
-11.500 -0.5753 0.01406 0.00868 -0.1045 0.8739 0.0257
-11.250 -0.5495 0.01370 0.00827 -0.1039 0.8688 0.0260
-11.000 -0.5235 0.01337 0.00788 -0.1034 0.8636 0.0263
-10.750 -0.4974 0.01305 0.00750 -0.1029 0.8589 0.0266
-10.500 -0.4712 0.01271 0.00711 -0.1024 0.8540 0.0268
-10.250 -0.4448 0.01240 0.00674 -0.1019 0.8487 0.0270
-9.750 -0.3916 0.01182 0.00605 -0.1010 0.8390 0.0275
-9.500 -0.3647 0.01156 0.00573 -0.1006 0.8338 0.0277
-9.250 -0.3378 0.01132 0.00543 -0.1002 0.8285 0.0278
-9.000 -0.3106 0.01109 0.00516 -0.0998 0.8236 0.0280
-8.750 -0.2837 0.01080 0.00483 -0.0995 0.8180 0.0283
-8.500 -0.2570 0.01052 0.00449 -0.0990 0.8125 0.0288
-8.250 -0.2298 0.01028 0.00422 -0.0987 0.8072 0.0293
-8.000 -0.2024 0.01006 0.00397 -0.0984 0.8012 0.0298
-7.750 -0.1751 0.00988 0.00375 -0.0981 0.7952 0.0302
-7.500 -0.1475 0.00970 0.00355 -0.0978 0.7894 0.0308
-7.250 -0.1199 0.00953 0.00335 -0.0975 0.7827 0.0313
-7.000 -0.0924 0.00940 0.00317 -0.0972 0.7761 0.0319
-6.750 -0.0646 0.00926 0.00301 -0.0970 0.7690 0.0325
-6.500 -0.0372 0.00914 0.00284 -0.0967 0.7613 0.0331
-6.250 -0.0096 0.00898 0.00267 -0.0964 0.7534 0.0343
-6.000 0.0175 0.00887 0.00252 -0.0961 0.7436 0.0357
-5.750 0.0445 0.00878 0.00238 -0.0957 0.7294 0.0373
-5.500 0.0709 0.00872 0.00225 -0.0952 0.7115 0.0397
-5.250 0.0972 0.00865 0.00213 -0.0947 0.6933 0.0445
-5.000 0.1233 0.00854 0.00203 -0.0943 0.6773 0.0552
-4.750 0.1493 0.00849 0.00195 -0.0937 0.6574 0.0669
-4.500 0.1750 0.00849 0.00189 -0.0932 0.6358 0.0753
-4.250 0.2013 0.00849 0.00184 -0.0927 0.6180 0.0822
-4.000 0.2280 0.00846 0.00180 -0.0924 0.6063 0.0901
-3.750 0.2546 0.00844 0.00176 -0.0921 0.5941 0.0994
-3.500 0.2813 0.00842 0.00173 -0.0917 0.5810 0.1097
-3.250 0.3079 0.00840 0.00171 -0.0914 0.5677 0.1227
-3.000 0.3343 0.00839 0.00170 -0.0911 0.5551 0.1372
-2.750 0.3609 0.00840 0.00170 -0.0908 0.5431 0.1499
-2.250 0.4139 0.00838 0.00171 -0.0902 0.5187 0.1831
-2.000 0.4400 0.00838 0.00173 -0.0898 0.5060 0.2061
-1.750 0.4660 0.00841 0.00177 -0.0895 0.4925 0.2285
-1.500 0.4922 0.00846 0.00181 -0.0891 0.4783 0.2456
-1.250 0.5183 0.00853 0.00186 -0.0888 0.4632 0.2589
-1.000 0.5441 0.00863 0.00192 -0.0884 0.4464 0.2720
-0.750 0.5695 0.00875 0.00200 -0.0880 0.4284 0.2865
-0.500 0.5949 0.00888 0.00208 -0.0876 0.4106 0.2997
-0.250 0.6203 0.00900 0.00217 -0.0872 0.3942 0.3163
0.000 0.6457 0.00911 0.00227 -0.0868 0.3787 0.3348
0.250 0.6711 0.00923 0.00236 -0.0864 0.3642 0.3506
0.500 0.6966 0.00935 0.00247 -0.0861 0.3510 0.3651
0.750 0.7220 0.00948 0.00257 -0.0857 0.3392 0.3806
1.000 0.7471 0.00960 0.00269 -0.0853 0.3278 0.4002
1.250 0.7727 0.00968 0.00280 -0.0850 0.3184 0.4250
1.500 0.7971 0.00968 0.00293 -0.0846 0.3097 0.4899
1.750 0.8107 0.00882 0.00312 -0.0818 0.3029 0.8842
2.000 0.8402 0.00893 0.00334 -0.0822 0.2947 0.9509
2.250 0.8795 0.00913 0.00352 -0.0849 0.2873 0.9766
2.500 0.9118 0.00936 0.00370 -0.0862 0.2798 0.9860
2.750 0.9438 0.00954 0.00385 -0.0874 0.2732 0.9927
3.250 1.0115 0.01000 0.00422 -0.0908 0.2567 0.9991
3.500 1.0366 0.01020 0.00438 -0.0906 0.2506 1.0000
3.750 1.0566 0.01038 0.00453 -0.0892 0.2461 1.0000
4.000 1.0777 0.01051 0.00467 -0.0881 0.2433 1.0000
4.250 1.0982 0.01067 0.00482 -0.0868 0.2393 1.0000
4.500 1.1180 0.01087 0.00499 -0.0855 0.2342 1.0000
4.750 1.1380 0.01108 0.00518 -0.0842 0.2299 1.0000
5.000 1.1596 0.01124 0.00535 -0.0832 0.2276 1.0000
5.250 1.1803 0.01141 0.00553 -0.0821 0.2250 1.0000
5.500 1.1998 0.01161 0.00573 -0.0807 0.2209 1.0000
5.750 1.2182 0.01189 0.00598 -0.0793 0.2151 1.0000
6.000 1.2390 0.01209 0.00619 -0.0783 0.2119 1.0000
6.250 1.2598 0.01232 0.00642 -0.0773 0.2077 1.0000
6.500 1.2794 0.01261 0.00670 -0.0762 0.2021 1.0000
6.750 1.2995 0.01290 0.00698 -0.0752 0.1971 1.0000
7.000 1.3200 0.01318 0.00726 -0.0743 0.1914 1.0000
7.250 1.3386 0.01357 0.00761 -0.0732 0.1840 1.0000
7.500 1.3578 0.01393 0.00796 -0.0722 0.1746 1.0000
7.750 1.3732 0.01450 0.00843 -0.0706 0.1577 1.0000
8.000 1.3835 0.01537 0.00913 -0.0684 0.1320 1.0000
8.250 1.3925 0.01633 0.00996 -0.0660 0.1106 1.0000
8.500 1.4053 0.01710 0.01068 -0.0643 0.0990 1.0000
8.750 1.4185 0.01786 0.01141 -0.0627 0.0898 1.0000
9.000 1.4318 0.01864 0.01215 -0.0611 0.0821 1.0000
9.250 1.4464 0.01934 0.01285 -0.0599 0.0759 1.0000
9.500 1.4593 0.02017 0.01365 -0.0585 0.0691 1.0000
9.750 1.4706 0.02112 0.01457 -0.0569 0.0603 1.0000
10.000 1.4777 0.02236 0.01573 -0.0549 0.0464 1.0000
10.250 1.4756 0.02427 0.01751 -0.0521 0.0273 1.0000
10.750 1.4897 0.02698 0.02022 -0.0489 0.0174 1.0000
11.000 1.4993 0.02820 0.02148 -0.0477 0.0158 1.0000
11.250 1.5087 0.02947 0.02279 -0.0465 0.0147 1.0000
11.500 1.5168 0.03087 0.02422 -0.0454 0.0137 1.0000
11.750 1.5255 0.03225 0.02565 -0.0444 0.0132 1.0000
12.000 1.5341 0.03369 0.02714 -0.0435 0.0127 1.0000
12.250 1.5416 0.03526 0.02877 -0.0427 0.0123 1.0000
12.500 1.5479 0.03699 0.03056 -0.0418 0.0118 1.0000
12.750 1.5530 0.03888 0.03250 -0.0411 0.0114 1.0000
13.000 1.5570 0.04095 0.03463 -0.0404 0.0110 1.0000
13.250 1.5603 0.04315 0.03690 -0.0398 0.0107 1.0000
13.500 1.5648 0.04531 0.03913 -0.0394 0.0105 1.0000
13.750 1.5681 0.04762 0.04151 -0.0391 0.0103 1.0000
14.000 1.5703 0.05012 0.04410 -0.0388 0.0100 1.0000
14.250 1.5714 0.05283 0.04687 -0.0387 0.0098 1.0000
14.500 1.5712 0.05574 0.04986 -0.0386 0.0095 1.0000
14.750 1.5697 0.05886 0.05306 -0.0387 0.0093 1.0000
15.000 1.5667 0.06222 0.05651 -0.0389 0.0091 1.0000
15.250 1.5621 0.06586 0.06023 -0.0392 0.0090 1.0000
15.500 1.5560 0.06979 0.06425 -0.0396 0.0088 1.0000
15.750 1.5480 0.07402 0.06857 -0.0402 0.0087 1.0000
16.000 1.5386 0.07850 0.07315 -0.0409 0.0085 1.0000
16.250 1.5290 0.08310 0.07785 -0.0417 0.0084 1.0000
16.500 1.5201 0.08768 0.08254 -0.0427 0.0083 1.0000
16.750 1.5099 0.09251 0.08747 -0.0438 0.0083 1.0000
17.000 1.4988 0.09750 0.09256 -0.0450 0.0082 1.0000
17.250 1.4875 0.10260 0.09776 -0.0464 0.0081 1.0000
17.500 1.4761 0.10778 0.10305 -0.0479 0.0081 1.0000
17.750 1.4647 0.11300 0.10837 -0.0495 0.0080 1.0000
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