Dormoy (dormoy-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: Dormoy (dormoy-il) Reynolds number: 200,000 Max Cl/Cd: 50.67 at α=2.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-dormoy-il-200000-n5.txt Download as CSV file: xf-dormoy-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3701 0.08845 0.08522 -0.0328 1.0000 0.0134
-9.250 -0.3708 0.08520 0.08203 -0.0340 1.0000 0.0134
-9.000 -0.3741 0.08210 0.07900 -0.0348 1.0000 0.0134
-8.750 -0.3792 0.07891 0.07588 -0.0359 1.0000 0.0134
-5.250 -0.0904 0.02170 0.01517 -0.0688 0.8784 0.0122
-5.000 -0.0612 0.01949 0.01256 -0.0686 0.8660 0.0112
-4.750 -0.0321 0.01788 0.01058 -0.0682 0.8532 0.0106
-4.500 -0.0038 0.01655 0.00897 -0.0677 0.8402 0.0101
-4.250 0.0236 0.01543 0.00764 -0.0671 0.8286 0.0102
-4.000 0.0502 0.01473 0.00678 -0.0664 0.8166 0.0121
-3.750 0.0758 0.01402 0.00594 -0.0656 0.8048 0.0130
-3.500 0.1005 0.01332 0.00516 -0.0647 0.7931 0.0135
-3.250 0.1245 0.01254 0.00421 -0.0638 0.7817 0.0147
-3.000 0.1495 0.01207 0.00354 -0.0631 0.7688 0.0192
-2.750 0.1751 0.01180 0.00304 -0.0623 0.7548 0.0225
-2.500 0.1982 0.01108 0.00272 -0.0614 0.7408 0.1700
-2.250 0.2167 0.00996 0.00258 -0.0601 0.7257 0.4510
-2.000 0.2329 0.00910 0.00254 -0.0575 0.7107 0.6940
-1.750 0.2951 0.00868 0.00248 -0.0638 0.6855 0.9544
-1.500 0.3327 0.00878 0.00229 -0.0658 0.6483 0.9783
-1.250 0.3676 0.00899 0.00212 -0.0674 0.5921 0.9939
-1.000 0.3957 0.00917 0.00205 -0.0676 0.5580 1.0000
-0.750 0.4175 0.00938 0.00204 -0.0665 0.5241 1.0000
-0.500 0.4380 0.00968 0.00205 -0.0652 0.4752 1.0000
-0.250 0.4566 0.01015 0.00213 -0.0636 0.4035 1.0000
0.000 0.4757 0.01066 0.00227 -0.0621 0.3485 1.0000
0.250 0.4973 0.01098 0.00241 -0.0611 0.3217 1.0000
0.500 0.5194 0.01128 0.00256 -0.0602 0.2980 1.0000
0.750 0.5418 0.01157 0.00273 -0.0594 0.2714 1.0000
1.000 0.5625 0.01203 0.00289 -0.0583 0.2050 1.0000
1.250 0.5828 0.01257 0.00316 -0.0572 0.1703 1.0000
1.500 0.6057 0.01287 0.00343 -0.0565 0.1613 1.0000
1.750 0.6296 0.01308 0.00367 -0.0559 0.1558 1.0000
2.000 0.6532 0.01334 0.00393 -0.0553 0.1496 1.0000
2.250 0.6771 0.01357 0.00419 -0.0548 0.1435 1.0000
2.500 0.7007 0.01383 0.00451 -0.0542 0.1321 1.0000
3.000 0.7412 0.01516 0.00556 -0.0520 0.0449 1.0000
3.250 0.7638 0.01557 0.00586 -0.0512 0.0170 1.0000
3.500 0.7862 0.01604 0.00651 -0.0503 0.0128 1.0000
3.750 0.8082 0.01658 0.00724 -0.0492 0.0112 1.0000
4.000 0.8295 0.01724 0.00809 -0.0480 0.0102 1.0000
4.250 0.8485 0.01813 0.00921 -0.0466 0.0089 1.0000
4.500 0.8597 0.01969 0.01100 -0.0441 0.0077 1.0000
4.750 0.8766 0.02062 0.01205 -0.0424 0.0072 1.0000
5.000 0.8907 0.02181 0.01338 -0.0403 0.0071 1.0000
5.250 0.9044 0.02319 0.01485 -0.0381 0.0070 1.0000
5.500 0.9191 0.02465 0.01639 -0.0362 0.0070 1.0000
5.750 0.9358 0.02644 0.01827 -0.0345 0.0069 1.0000
6.000 0.9556 0.02837 0.02030 -0.0334 0.0070 1.0000
6.250 0.9788 0.03100 0.02305 -0.0327 0.0072 1.0000
6.500 1.0001 0.03323 0.02550 -0.0317 0.0070 1.0000
6.750 1.0192 0.03563 0.02815 -0.0304 0.0070 1.0000
7.000 1.0347 0.03672 0.02951 -0.0287 0.0057 1.0000
7.250 1.0492 0.03943 0.03251 -0.0269 0.0057 1.0000
7.500 1.0599 0.04294 0.03643 -0.0247 0.0062 1.0000
7.750 1.0646 0.04651 0.04030 -0.0224 0.0067 1.0000
12.750 0.8517 0.15279 0.14943 -0.0474 0.0141 1.0000
14.250 0.8639 0.18830 0.18483 -0.0643 0.0138 1.0000
15.250 0.6947 0.18431 0.18137 -0.0612 0.0141 1.0000
15.500 0.6954 0.18915 0.18618 -0.0632 0.0139 1.0000
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Polar data table (+)
Polar graphs
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