Dormoy (dormoy-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: Dormoy (dormoy-il) Reynolds number: 200,000 Max Cl/Cd: 57.43 at α=2° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-dormoy-il-200000.txt Download as CSV file: xf-dormoy-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4093 0.08759 0.08440 -0.0356 1.0000 0.0258
-9.500 -0.4076 0.08424 0.08101 -0.0309 1.0000 0.0285
-9.250 -0.4089 0.08128 0.07811 -0.0313 1.0000 0.0295
-9.000 -0.4151 0.07818 0.07509 -0.0320 1.0000 0.0302
-8.750 -0.4204 0.07480 0.07176 -0.0335 1.0000 0.0305
-8.500 -0.4225 0.07104 0.06803 -0.0355 1.0000 0.0309
-8.250 -0.4241 0.06717 0.06417 -0.0372 1.0000 0.0318
-8.000 -0.4250 0.06341 0.06039 -0.0381 1.0000 0.0327
-7.750 -0.4262 0.05985 0.05680 -0.0382 1.0000 0.0337
-7.500 -0.4301 0.05667 0.05355 -0.0371 1.0000 0.0349
-7.250 -0.4355 0.05412 0.05086 -0.0349 1.0000 0.0362
-6.250 -0.3312 0.03692 0.03270 -0.0483 0.9796 0.0565
-6.000 -0.2990 0.03378 0.02927 -0.0511 0.9725 0.0691
-5.750 -0.2662 0.03135 0.02655 -0.0540 0.9664 0.0932
-4.750 -0.1100 0.01908 0.01191 -0.0570 0.9443 0.0398
-4.500 -0.0703 0.01718 0.00987 -0.0582 0.9384 0.0344
-4.250 -0.0324 0.01593 0.00849 -0.0595 0.9311 0.0365
-4.000 0.0008 0.01447 0.00702 -0.0599 0.9224 0.0352
-3.750 0.0361 0.01339 0.00587 -0.0609 0.9143 0.0348
-3.500 0.0665 0.01272 0.00506 -0.0609 0.9031 0.0355
-3.250 0.0967 0.01222 0.00439 -0.0609 0.8915 0.0382
-3.000 0.1237 0.01135 0.00381 -0.0604 0.8790 0.1352
-2.750 0.1446 0.01009 0.00358 -0.0593 0.8662 0.4241
-2.500 0.2090 0.00861 0.00366 -0.0649 0.8567 0.9584
-2.250 0.2892 0.00857 0.00335 -0.0756 0.8442 1.0000
-2.000 0.3117 0.00859 0.00321 -0.0744 0.8281 1.0000
-1.750 0.3336 0.00864 0.00307 -0.0730 0.8095 1.0000
-1.500 0.3552 0.00869 0.00295 -0.0715 0.7900 1.0000
-1.250 0.3763 0.00873 0.00285 -0.0700 0.7689 1.0000
-1.000 0.3987 0.00878 0.00279 -0.0688 0.7528 1.0000
-0.750 0.4210 0.00882 0.00275 -0.0676 0.7353 1.0000
-0.500 0.4434 0.00886 0.00272 -0.0664 0.7165 1.0000
-0.250 0.4656 0.00891 0.00267 -0.0652 0.6945 1.0000
0.000 0.4875 0.00899 0.00261 -0.0639 0.6665 1.0000
0.250 0.5082 0.00913 0.00254 -0.0623 0.6268 1.0000
0.500 0.5289 0.00933 0.00253 -0.0608 0.5844 1.0000
0.750 0.5491 0.00961 0.00260 -0.0592 0.5376 1.0000
1.000 0.5694 0.00992 0.00269 -0.0578 0.4908 1.0000
1.250 0.5896 0.01027 0.00281 -0.0564 0.4439 1.0000
1.500 0.6096 0.01067 0.00298 -0.0550 0.4000 1.0000
1.750 0.6304 0.01105 0.00319 -0.0539 0.3692 1.0000
2.000 0.6524 0.01136 0.00342 -0.0529 0.3484 1.0000
2.250 0.6728 0.01181 0.00374 -0.0517 0.3173 1.0000
2.500 0.6934 0.01227 0.00400 -0.0507 0.2746 1.0000
2.750 0.7151 0.01266 0.00423 -0.0498 0.2272 1.0000
3.000 0.7316 0.01358 0.00468 -0.0482 0.1657 1.0000
3.250 0.7534 0.01403 0.00509 -0.0473 0.1489 1.0000
3.500 0.7763 0.01439 0.00551 -0.0466 0.1310 1.0000
3.750 0.7932 0.01539 0.00624 -0.0450 0.0638 1.0000
4.000 0.8133 0.01609 0.00704 -0.0437 0.0485 1.0000
4.250 0.8362 0.01650 0.00759 -0.0428 0.0368 1.0000
4.500 0.8582 0.01704 0.00818 -0.0417 0.0275 1.0000
4.750 0.8784 0.01780 0.00906 -0.0403 0.0250 1.0000
5.000 0.8965 0.01876 0.01024 -0.0386 0.0241 1.0000
5.250 0.9129 0.01976 0.01144 -0.0367 0.0222 1.0000
5.500 0.9257 0.02101 0.01277 -0.0345 0.0198 1.0000
5.750 0.9373 0.02242 0.01426 -0.0320 0.0198 1.0000
6.000 0.9499 0.02417 0.01607 -0.0296 0.0198 1.0000
6.250 0.9696 0.02640 0.01834 -0.0280 0.0207 1.0000
6.500 1.0041 0.03018 0.02219 -0.0283 0.0235 1.0000
12.500 0.6900 0.14549 0.14246 -0.0381 0.0554 1.0000
12.750 0.6853 0.15012 0.14709 -0.0408 0.0540 1.0000
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Polar data table (+)
Polar graphs
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