Dormoy (dormoy-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: Dormoy (dormoy-il) Reynolds number: 100,000 Max Cl/Cd: 50.35 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-dormoy-il-100000.txt Download as CSV file: xf-dormoy-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: Dormoy
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.3311 0.11610 0.11149 -0.0223 1.0000 0.0738
-11.750 -0.3382 0.11363 0.10906 -0.0247 1.0000 0.0758
-11.500 -0.3493 0.11132 0.10682 -0.0277 1.0000 0.0766
-11.250 -0.3280 0.10555 0.10104 -0.0250 1.0000 0.0806
-11.000 -0.3240 0.10221 0.09773 -0.0253 1.0000 0.0853
-10.750 -0.3305 0.09921 0.09479 -0.0273 1.0000 0.0887
-10.500 -0.3454 0.09661 0.09227 -0.0307 1.0000 0.0899
-10.250 -0.3226 0.09165 0.08730 -0.0274 1.0000 0.0960
-10.000 -0.3279 0.08851 0.08422 -0.0289 1.0000 0.1009
-9.750 -0.3468 0.08583 0.08165 -0.0324 1.0000 0.1025
-9.500 -0.3246 0.08130 0.07711 -0.0289 1.0000 0.1098
-9.250 -0.3372 0.07842 0.07432 -0.0308 1.0000 0.1141
-9.000 -0.3608 0.07590 0.07194 -0.0333 1.0000 0.1151
-8.750 -0.3362 0.07149 0.06753 -0.0295 1.0000 0.1240
-8.500 -0.3569 0.06905 0.06522 -0.0302 1.0000 0.1268
-8.250 -0.3826 0.06617 0.06244 -0.0336 1.0000 0.1281
-8.000 -0.4241 0.07324 0.06918 -0.0312 1.0000 0.1237
-7.750 -0.4373 0.06977 0.06564 -0.0366 1.0000 0.1295
-7.500 -0.4256 0.06727 0.06327 -0.0316 1.0000 0.1381
-7.250 -0.4297 0.06410 0.06010 -0.0319 1.0000 0.1450
-7.000 -0.4387 0.06279 0.05854 -0.0333 1.0000 0.1560
-6.750 -0.4302 0.05935 0.05539 -0.0277 1.0000 0.1616
-6.500 -0.4324 0.05680 0.05277 -0.0270 1.0000 0.1724
-6.250 -0.4306 0.05442 0.05031 -0.0260 1.0000 0.1852
-6.000 -0.4259 0.05200 0.04784 -0.0245 1.0000 0.1988
-5.750 -0.4193 0.04945 0.04529 -0.0226 1.0000 0.2134
-4.750 -0.3164 0.02986 0.02264 -0.0255 1.0000 0.0754
-4.500 -0.2913 0.02694 0.01919 -0.0245 0.9997 0.0665
-4.250 -0.2456 0.02530 0.01697 -0.0270 0.9932 0.0616
-4.000 -0.2022 0.02304 0.01438 -0.0291 0.9864 0.0577
-3.750 -0.1568 0.02152 0.01262 -0.0315 0.9790 0.0545
-3.500 -0.1125 0.02035 0.01139 -0.0341 0.9707 0.0540
-3.250 -0.0731 0.01948 0.01045 -0.0362 0.9612 0.0560
-3.000 -0.0307 0.01871 0.00953 -0.0388 0.9525 0.0688
-2.750 0.0106 0.01764 0.00899 -0.0412 0.9436 0.1939
-2.500 0.0984 0.01507 0.00882 -0.0516 0.9445 1.0000
-2.250 0.1481 0.01498 0.00835 -0.0558 0.9325 1.0000
-2.000 0.2002 0.01477 0.00789 -0.0603 0.9210 1.0000
-1.750 0.2519 0.01449 0.00741 -0.0646 0.9101 1.0000
-1.500 0.2990 0.01419 0.00696 -0.0680 0.8991 1.0000
-1.250 0.3420 0.01392 0.00658 -0.0705 0.8877 1.0000
-1.000 0.3765 0.01378 0.00636 -0.0714 0.8748 1.0000
-0.750 0.4088 0.01367 0.00618 -0.0718 0.8611 1.0000
-0.500 0.4362 0.01358 0.00604 -0.0710 0.8431 1.0000
-0.250 0.4642 0.01339 0.00574 -0.0700 0.8218 1.0000
0.000 0.4874 0.01332 0.00558 -0.0682 0.7985 1.0000
0.250 0.5110 0.01328 0.00546 -0.0666 0.7768 1.0000
0.500 0.5329 0.01332 0.00547 -0.0650 0.7561 1.0000
0.750 0.5556 0.01334 0.00549 -0.0635 0.7357 1.0000
1.000 0.5776 0.01332 0.00543 -0.0618 0.7116 1.0000
1.250 0.5991 0.01331 0.00536 -0.0601 0.6840 1.0000
1.500 0.6210 0.01335 0.00535 -0.0585 0.6553 1.0000
1.750 0.6430 0.01345 0.00540 -0.0571 0.6254 1.0000
2.000 0.6648 0.01361 0.00547 -0.0556 0.5925 1.0000
2.250 0.6861 0.01384 0.00565 -0.0542 0.5570 1.0000
2.500 0.7073 0.01413 0.00583 -0.0528 0.5221 1.0000
2.750 0.7286 0.01447 0.00609 -0.0515 0.4889 1.0000
3.000 0.7463 0.01493 0.00626 -0.0496 0.4355 1.0000
3.250 0.7653 0.01544 0.00657 -0.0481 0.3944 1.0000
3.500 0.7858 0.01593 0.00705 -0.0469 0.3668 1.0000
3.750 0.8041 0.01656 0.00750 -0.0454 0.3272 1.0000
4.000 0.8237 0.01713 0.00800 -0.0441 0.2894 1.0000
4.250 0.8436 0.01771 0.00848 -0.0429 0.2251 1.0000
4.500 0.8560 0.01922 0.00937 -0.0406 0.1354 1.0000
4.750 0.8612 0.02193 0.01170 -0.0372 0.0595 1.0000
5.000 0.8735 0.02360 0.01358 -0.0348 0.0490 1.0000
5.250 0.8855 0.02509 0.01525 -0.0323 0.0452 1.0000
5.500 0.8984 0.02645 0.01680 -0.0299 0.0424 1.0000
5.750 0.9122 0.02793 0.01831 -0.0277 0.0409 1.0000
6.000 0.9318 0.02977 0.02007 -0.0262 0.0396 1.0000
6.250 0.9622 0.03208 0.02229 -0.0261 0.0389 1.0000
6.500 0.9988 0.03591 0.02591 -0.0276 0.0363 1.0000
6.750 1.0235 0.03854 0.02877 -0.0269 0.0352 1.0000
7.000 1.0536 0.04207 0.03246 -0.0269 0.0363 1.0000
7.250 1.0668 0.04254 0.03367 -0.0233 0.0395 1.0000
7.500 1.0854 0.04611 0.03769 -0.0215 0.0437 1.0000
7.750 1.1177 0.04884 0.04098 -0.0196 0.0612 1.0000
8.000 1.1315 0.05115 0.04466 -0.0147 0.0873 1.0000
8.250 1.1240 0.05712 0.05134 -0.0111 0.1004 1.0000
8.500 1.1127 0.06232 0.05701 -0.0083 0.1074 1.0000
8.750 1.0837 0.06673 0.06178 -0.0051 0.1093 1.0000
9.000 1.0562 0.07043 0.06567 -0.0022 0.1098 1.0000
9.250 1.0271 0.07456 0.06995 -0.0011 0.1098 1.0000
9.500 0.9991 0.07936 0.07485 -0.0020 0.1091 1.0000
9.750 0.9709 0.08528 0.08084 -0.0047 0.1082 1.0000
10.000 0.9452 0.09227 0.08787 -0.0088 0.1073 1.0000
10.250 0.9173 0.10125 0.09684 -0.0147 0.1066 1.0000
10.500 0.8879 0.11248 0.10799 -0.0223 0.1065 1.0000
10.750 0.8582 0.12364 0.11904 -0.0299 0.1081 1.0000
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Polar data table (+)
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