Dormoy (dormoy-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: Dormoy (dormoy-il) Reynolds number: 1,000,000 Max Cl/Cd: 104.12 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-dormoy-il-1000000.txt Download as CSV file: xf-dormoy-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.4099 0.10166 0.10007 -0.0217 1.0000 0.0042
-10.750 -0.4072 0.09788 0.09631 -0.0231 1.0000 0.0042
-10.500 -0.4049 0.09409 0.09254 -0.0245 1.0000 0.0042
-7.750 -0.3461 0.04282 0.04096 -0.0618 0.9717 0.0062
-7.500 -0.3046 0.03918 0.03704 -0.0647 0.9630 0.0077
-7.250 -0.2716 0.03475 0.03228 -0.0689 0.9456 0.0077
-7.000 -0.2427 0.03118 0.02831 -0.0712 0.9095 0.0078
-6.750 -0.2249 0.02894 0.02564 -0.0700 0.8682 0.0078
-6.500 -0.2085 0.02678 0.02312 -0.0684 0.8440 0.0078
-6.250 -0.1901 0.02471 0.02073 -0.0671 0.8300 0.0078
-5.750 -0.1570 0.01729 0.01258 -0.0639 0.8092 0.0089
-5.500 -0.1336 0.01598 0.01112 -0.0632 0.7993 0.0093
-5.250 -0.1094 0.01487 0.00983 -0.0624 0.7906 0.0099
-5.000 -0.0844 0.01388 0.00868 -0.0617 0.7818 0.0106
-4.750 -0.0586 0.01300 0.00767 -0.0611 0.7734 0.0115
-4.500 -0.0323 0.01241 0.00696 -0.0604 0.7646 0.0131
-4.250 -0.0072 0.01023 0.00453 -0.0587 0.7555 0.0087
-4.000 0.0172 0.00947 0.00374 -0.0579 0.7452 0.0101
-3.750 0.0424 0.00900 0.00319 -0.0572 0.7337 0.0111
-3.500 0.0673 0.00863 0.00271 -0.0565 0.7142 0.0119
-3.250 0.0918 0.00843 0.00237 -0.0557 0.6836 0.0132
-3.000 0.1160 0.00818 0.00191 -0.0548 0.6481 0.0133
-2.750 0.1403 0.00807 0.00159 -0.0539 0.6097 0.0141
-2.500 0.1650 0.00800 0.00128 -0.0532 0.5723 0.0163
-2.250 0.1894 0.00811 0.00111 -0.0525 0.5204 0.0193
-2.000 0.2117 0.00796 0.00101 -0.0515 0.4595 0.1347
-1.750 0.2331 0.00822 0.00108 -0.0506 0.3655 0.1940
-1.500 0.2540 0.00785 0.00111 -0.0497 0.3277 0.3873
-1.250 0.2753 0.00742 0.00114 -0.0487 0.3061 0.5672
-1.000 0.2905 0.00676 0.00122 -0.0461 0.2915 0.8152
-0.750 0.3247 0.00665 0.00135 -0.0473 0.2653 0.9531
-0.500 0.3634 0.00731 0.00155 -0.0502 0.1635 0.9716
-0.250 0.4005 0.00751 0.00166 -0.0524 0.1492 0.9828
0.000 0.4380 0.00769 0.00174 -0.0547 0.1371 0.9889
0.250 0.4710 0.00816 0.00192 -0.0562 0.0694 0.9947
0.500 0.5101 0.00833 0.00202 -0.0590 0.0587 0.9985
0.750 0.5421 0.00846 0.00216 -0.0601 0.0565 1.0000
1.000 0.5650 0.00863 0.00232 -0.0592 0.0530 1.0000
1.250 0.5876 0.00884 0.00255 -0.0582 0.0482 1.0000
1.500 0.6110 0.00899 0.00270 -0.0575 0.0471 1.0000
1.750 0.6353 0.00906 0.00272 -0.0569 0.0460 1.0000
2.000 0.6594 0.00917 0.00281 -0.0563 0.0441 1.0000
2.250 0.6834 0.00929 0.00290 -0.0557 0.0401 1.0000
2.500 0.7072 0.00944 0.00301 -0.0550 0.0341 1.0000
2.750 0.7292 0.00979 0.00325 -0.0540 0.0137 1.0000
3.000 0.7528 0.01001 0.00353 -0.0532 0.0118 1.0000
3.250 0.7760 0.01029 0.00391 -0.0523 0.0100 1.0000
3.500 0.7988 0.01061 0.00431 -0.0514 0.0095 1.0000
3.750 0.8212 0.01096 0.00471 -0.0505 0.0087 1.0000
4.000 0.8430 0.01139 0.00521 -0.0494 0.0081 1.0000
4.250 0.8641 0.01189 0.00578 -0.0482 0.0073 1.0000
4.500 0.8838 0.01253 0.00649 -0.0468 0.0065 1.0000
4.750 0.8998 0.01353 0.00758 -0.0447 0.0058 1.0000
5.000 0.9140 0.01467 0.00884 -0.0424 0.0057 1.0000
5.250 0.9307 0.01561 0.00986 -0.0404 0.0058 1.0000
5.500 0.9100 0.00874 0.00349 -0.0332 0.0102 1.0000
5.750 0.9321 0.01041 0.00525 -0.0324 0.0102 1.0000
6.000 0.9530 0.01192 0.00688 -0.0314 0.0101 1.0000
6.250 0.9716 0.01020 0.00522 -0.0301 0.0082 1.0000
6.500 0.9900 0.01121 0.00629 -0.0291 0.0072 1.0000
6.750 1.0080 0.01273 0.00790 -0.0280 0.0067 1.0000
7.000 1.0250 0.01436 0.00958 -0.0270 0.0062 1.0000
7.250 1.0405 0.01735 0.01267 -0.0261 0.0056 1.0000
7.750 1.0824 0.03945 0.03523 -0.0232 0.0051 1.0000
8.000 1.0843 0.04229 0.03833 -0.0201 0.0051 1.0000
8.250 1.0841 0.04501 0.04128 -0.0170 0.0051 1.0000
8.500 1.0807 0.04759 0.04408 -0.0137 0.0051 1.0000
8.750 1.0725 0.04979 0.04647 -0.0099 0.0050 1.0000
9.000 1.0601 0.05217 0.04899 -0.0058 0.0051 1.0000
9.250 1.0824 0.05101 0.04795 -0.0040 0.0043 1.0000
9.500 1.0727 0.05374 0.05083 -0.0012 0.0042 1.0000
9.750 1.0620 0.05667 0.05391 0.0009 0.0040 1.0000
10.000 1.0457 0.06007 0.05745 0.0021 0.0040 1.0000
10.250 1.0310 0.06374 0.06125 0.0024 0.0038 1.0000
10.500 1.0107 0.06831 0.06596 0.0016 0.0040 1.0000
10.750 0.9950 0.07300 0.07077 0.0000 0.0037 1.0000
11.000 0.9739 0.07887 0.07676 -0.0029 0.0040 1.0000
11.250 0.9546 0.08525 0.08326 -0.0066 0.0040 1.0000
11.500 0.9310 0.09309 0.09121 -0.0117 0.0042 1.0000
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Polar data table (+)
Polar graphs
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