Dormoy (dormoy-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: Dormoy (dormoy-il) Reynolds number: 100,000 Max Cl/Cd: 45.83 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-dormoy-il-100000-n5.txt Download as CSV file: xf-dormoy-il-100000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3707 0.09147 0.08688 -0.0303 1.0000 0.0206
-9.250 -0.3712 0.08826 0.08374 -0.0313 1.0000 0.0209
-9.000 -0.3732 0.08519 0.08075 -0.0321 1.0000 0.0208
-8.750 -0.3779 0.08225 0.07790 -0.0326 1.0000 0.0209
-8.500 -0.3831 0.07919 0.07493 -0.0334 1.0000 0.0210
-8.250 -0.3855 0.07566 0.07148 -0.0351 1.0000 0.0213
-8.000 -0.3866 0.07226 0.06812 -0.0364 1.0000 0.0211
-7.750 -0.3878 0.06882 0.06472 -0.0373 1.0000 0.0214
-7.500 -0.3893 0.06557 0.06146 -0.0374 1.0000 0.0215
-7.250 -0.3918 0.06256 0.05843 -0.0368 1.0000 0.0216
-7.000 -0.3743 0.05776 0.05349 -0.0408 0.9949 0.0221
-6.750 -0.3445 0.05228 0.04773 -0.0464 0.9866 0.0225
-6.500 -0.3158 0.04714 0.04228 -0.0505 0.9780 0.0221
-6.250 -0.2861 0.04230 0.03706 -0.0529 0.9695 0.0147
-6.000 -0.2571 0.03810 0.03243 -0.0550 0.9611 0.0131
-5.750 -0.2246 0.03425 0.02802 -0.0568 0.9545 0.0123
-5.500 -0.1963 0.03164 0.02492 -0.0576 0.9458 0.0154
-5.250 -0.1629 0.02879 0.02144 -0.0594 0.9405 0.0198
-5.000 -0.1318 0.02742 0.01943 -0.0595 0.9315 0.0248
-4.750 -0.0982 0.02443 0.01612 -0.0603 0.9254 0.0231
-4.500 -0.0655 0.02240 0.01376 -0.0605 0.9171 0.0224
-4.250 -0.0321 0.02068 0.01180 -0.0607 0.9088 0.0227
-4.000 0.0025 0.01921 0.01018 -0.0613 0.9011 0.0237
-3.750 0.0310 0.01777 0.00870 -0.0612 0.8909 0.0280
-3.500 0.0616 0.01686 0.00760 -0.0614 0.8816 0.0335
-3.250 0.0948 0.01622 0.00668 -0.0620 0.8732 0.0340
-3.000 0.1249 0.01578 0.00588 -0.0620 0.8620 0.0347
-2.750 0.1551 0.01542 0.00534 -0.0620 0.8504 0.0364
-2.250 0.2132 0.01446 0.00462 -0.0620 0.8248 0.1951
-2.000 0.2392 0.01346 0.00443 -0.0619 0.8106 0.4465
-1.750 0.3221 0.01195 0.00422 -0.0717 0.7946 1.0000
-1.500 0.3468 0.01201 0.00409 -0.0710 0.7794 1.0000
-1.250 0.3708 0.01208 0.00402 -0.0701 0.7654 1.0000
-1.000 0.3940 0.01215 0.00396 -0.0691 0.7489 1.0000
-0.750 0.4162 0.01221 0.00387 -0.0678 0.7252 1.0000
-0.500 0.4380 0.01226 0.00376 -0.0664 0.6965 1.0000
-0.250 0.4601 0.01233 0.00368 -0.0650 0.6654 1.0000
0.000 0.4827 0.01245 0.00362 -0.0638 0.6344 1.0000
0.250 0.5056 0.01259 0.00360 -0.0628 0.6054 1.0000
0.500 0.5277 0.01280 0.00360 -0.0616 0.5673 1.0000
0.750 0.5491 0.01308 0.00363 -0.0603 0.5215 1.0000
1.000 0.5706 0.01339 0.00374 -0.0591 0.4802 1.0000
1.250 0.5924 0.01372 0.00401 -0.0581 0.4432 1.0000
1.500 0.6140 0.01409 0.00422 -0.0570 0.4093 1.0000
1.750 0.6357 0.01447 0.00447 -0.0561 0.3818 1.0000
2.000 0.6577 0.01485 0.00476 -0.0552 0.3606 1.0000
2.250 0.6803 0.01519 0.00508 -0.0544 0.3446 1.0000
2.500 0.7028 0.01556 0.00544 -0.0536 0.3275 1.0000
2.750 0.7248 0.01598 0.00584 -0.0528 0.3075 1.0000
3.000 0.7479 0.01632 0.00627 -0.0521 0.2919 1.0000
3.250 0.7619 0.01752 0.00674 -0.0503 0.1778 1.0000
3.500 0.7720 0.01950 0.00813 -0.0480 0.0533 1.0000
3.750 0.7957 0.01984 0.00864 -0.0473 0.0375 1.0000
4.000 0.8150 0.02076 0.00949 -0.0459 0.0164 1.0000
4.250 0.8349 0.02163 0.01052 -0.0446 0.0147 1.0000
4.500 0.8548 0.02251 0.01162 -0.0432 0.0138 1.0000
4.750 0.8733 0.02353 0.01289 -0.0417 0.0131 1.0000
5.000 0.8899 0.02469 0.01431 -0.0399 0.0127 1.0000
5.250 0.9035 0.02601 0.01588 -0.0378 0.0122 1.0000
5.500 0.9131 0.02751 0.01757 -0.0354 0.0107 1.0000
5.750 0.9155 0.02954 0.01968 -0.0322 0.0095 1.0000
6.000 0.9271 0.03094 0.02122 -0.0301 0.0080 1.0000
6.250 0.9397 0.03249 0.02286 -0.0281 0.0071 1.0000
6.500 0.9560 0.03447 0.02490 -0.0266 0.0069 1.0000
6.750 0.9779 0.03665 0.02720 -0.0257 0.0069 1.0000
7.000 1.0014 0.03925 0.03000 -0.0250 0.0070 1.0000
7.250 1.0228 0.04213 0.03338 -0.0241 0.0074 1.0000
7.500 1.0380 0.04514 0.03672 -0.0226 0.0076 1.0000
7.750 1.0475 0.04817 0.04008 -0.0207 0.0078 1.0000
8.000 1.0523 0.05129 0.04353 -0.0184 0.0080 1.0000
8.250 1.0521 0.05445 0.04698 -0.0160 0.0082 1.0000
8.500 1.0475 0.05744 0.05023 -0.0132 0.0084 1.0000
8.750 1.0399 0.06062 0.05364 -0.0108 0.0086 1.0000
9.000 1.0307 0.06405 0.05728 -0.0089 0.0088 1.0000
9.250 1.0290 0.06846 0.06181 -0.0081 0.0092 1.0000
9.500 1.0189 0.07083 0.06442 -0.0068 0.0093 1.0000
9.750 1.0065 0.07360 0.06749 -0.0061 0.0097 1.0000
10.000 0.9902 0.07765 0.07182 -0.0067 0.0099 1.0000
10.250 0.9741 0.08242 0.07684 -0.0082 0.0102 1.0000
10.500 0.9572 0.08788 0.08248 -0.0106 0.0103 1.0000
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Polar data table (+)
Polar graphs
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