Dormoy (dormoy-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: Dormoy (dormoy-il) Reynolds number: 50,000 Max Cl/Cd: 36.54 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-dormoy-il-50000.txt Download as CSV file: xf-dormoy-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4042 0.10551 0.09902 -0.0148 1.0000 0.2324
-9.750 -0.4018 0.10238 0.09598 -0.0148 1.0000 0.2438
-9.500 -0.4225 0.10198 0.09575 -0.0162 1.0000 0.2517
-9.250 -0.4138 0.09825 0.09207 -0.0152 1.0000 0.2650
-9.000 -0.4120 0.09519 0.08910 -0.0143 1.0000 0.2787
-8.750 -0.4084 0.09209 0.08608 -0.0133 1.0000 0.2921
-8.500 -0.4056 0.08904 0.08311 -0.0120 1.0000 0.3054
-8.250 -0.4041 0.08605 0.08021 -0.0106 1.0000 0.3186
-8.000 -0.4066 0.08349 0.07776 -0.0088 1.0000 0.3324
-7.750 -0.4171 0.08151 0.07595 -0.0075 1.0000 0.3478
-7.500 -0.4058 0.07770 0.07219 -0.0052 1.0000 0.3635
-7.250 -0.3988 0.07461 0.06918 -0.0029 1.0000 0.3809
-7.000 -0.4067 0.07258 0.06729 -0.0002 1.0000 0.4044
-5.750 -0.3782 0.04563 0.03879 -0.0324 1.0000 0.1387
-5.500 -0.3605 0.04137 0.03400 -0.0322 1.0000 0.1209
-5.250 -0.3408 0.03776 0.02979 -0.0314 1.0000 0.1094
-5.000 -0.3191 0.03465 0.02593 -0.0304 1.0000 0.1008
-4.750 -0.2974 0.03200 0.02288 -0.0292 1.0000 0.0959
-4.500 -0.2725 0.02965 0.01972 -0.0279 1.0000 0.0912
-4.250 -0.2490 0.02805 0.01774 -0.0266 1.0000 0.0898
-4.000 -0.2250 0.02641 0.01591 -0.0254 1.0000 0.0911
-3.750 -0.2020 0.02520 0.01468 -0.0244 1.0000 0.0977
-3.500 -0.1786 0.02431 0.01353 -0.0231 1.0000 0.1029
-3.250 -0.1563 0.02349 0.01270 -0.0221 1.0000 0.1100
-3.000 -0.1340 0.02287 0.01206 -0.0211 1.0000 0.1259
-2.750 -0.1101 0.02187 0.01146 -0.0206 1.0000 0.2013
-2.500 -0.0669 0.01912 0.01111 -0.0219 1.0000 1.0000
-2.250 -0.0492 0.01947 0.01099 -0.0208 1.0000 1.0000
-2.000 -0.0317 0.01985 0.01098 -0.0198 1.0000 1.0000
-1.750 -0.0144 0.02028 0.01108 -0.0190 1.0000 1.0000
-1.500 0.0029 0.02075 0.01126 -0.0183 1.0000 1.0000
-1.250 0.0200 0.02126 0.01153 -0.0177 1.0000 1.0000
-1.000 0.0369 0.02183 0.01183 -0.0172 1.0000 1.0000
-0.750 0.0934 0.02303 0.01275 -0.0242 0.9834 1.0000
-0.500 0.1459 0.02402 0.01355 -0.0302 0.9658 1.0000
-0.250 0.1961 0.02485 0.01422 -0.0355 0.9470 1.0000
0.000 0.2515 0.02563 0.01491 -0.0415 0.9287 1.0000
0.250 0.2953 0.02618 0.01543 -0.0452 0.9077 1.0000
0.500 0.3542 0.02656 0.01585 -0.0510 0.8875 1.0000
0.750 0.4042 0.02671 0.01606 -0.0549 0.8634 1.0000
1.000 0.4614 0.02653 0.01599 -0.0593 0.8388 1.0000
1.250 0.5165 0.02609 0.01575 -0.0626 0.8144 1.0000
1.500 0.5662 0.02555 0.01535 -0.0646 0.7901 1.0000
1.750 0.6051 0.02499 0.01489 -0.0644 0.7619 1.0000
2.000 0.6376 0.02444 0.01442 -0.0630 0.7320 1.0000
2.250 0.6674 0.02390 0.01394 -0.0612 0.7026 1.0000
2.500 0.6955 0.02334 0.01352 -0.0591 0.6732 1.0000
2.750 0.7216 0.02304 0.01326 -0.0573 0.6449 1.0000
3.000 0.7463 0.02301 0.01326 -0.0556 0.6179 1.0000
3.250 0.7701 0.02322 0.01356 -0.0541 0.5927 1.0000
3.500 0.7944 0.02358 0.01410 -0.0530 0.5697 1.0000
3.750 0.8182 0.02380 0.01439 -0.0515 0.5451 1.0000
4.000 0.8367 0.02356 0.01406 -0.0485 0.5077 1.0000
4.250 0.8569 0.02385 0.01444 -0.0466 0.4803 1.0000
4.500 0.8745 0.02411 0.01480 -0.0443 0.4499 1.0000
4.750 0.8816 0.02413 0.01460 -0.0401 0.3976 1.0000
5.000 0.8908 0.02458 0.01502 -0.0366 0.3497 1.0000
5.250 0.8975 0.02531 0.01554 -0.0328 0.2766 1.0000
5.500 0.9027 0.02702 0.01654 -0.0294 0.1572 1.0000
5.750 0.9107 0.02932 0.01822 -0.0270 0.0950 1.0000
6.000 0.9182 0.03152 0.02032 -0.0245 0.0861 1.0000
6.250 0.9232 0.03376 0.02259 -0.0217 0.0806 1.0000
6.500 0.9301 0.03587 0.02483 -0.0191 0.0755 1.0000
6.750 0.9426 0.03852 0.02743 -0.0171 0.0709 1.0000
7.000 0.9802 0.04073 0.02977 -0.0168 0.0694 1.0000
7.250 1.0276 0.04381 0.03305 -0.0177 0.0692 1.0000
7.500 1.0692 0.04794 0.03740 -0.0185 0.0702 1.0000
7.750 1.0895 0.05012 0.04013 -0.0167 0.0721 1.0000
8.000 1.0977 0.05269 0.04349 -0.0139 0.0750 1.0000
8.250 1.1053 0.05652 0.04802 -0.0117 0.0781 1.0000
8.500 1.1140 0.06097 0.05283 -0.0101 0.0807 1.0000
8.750 1.1261 0.06606 0.05817 -0.0092 0.0827 1.0000
9.000 1.0989 0.06846 0.06122 -0.0052 0.0846 1.0000
9.250 1.0688 0.07206 0.06519 -0.0021 0.0863 1.0000
9.500 1.0416 0.07622 0.06959 -0.0007 0.0875 1.0000
9.750 1.0142 0.08112 0.07466 -0.0013 0.0883 1.0000
10.000 0.9861 0.08686 0.08042 -0.0035 0.0889 1.0000
10.250 0.9548 0.09396 0.08759 -0.0077 0.0890 1.0000
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Polar data table (+)
Polar graphs
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