ONERA OA206 AIRFOIL (oa206-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: ONERA OA206 AIRFOIL (oa206-il) Reynolds number: 100,000 Max Cl/Cd: 36.37 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-oa206-il-100000.txt Download as CSV file: xf-oa206-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: ONERA OA206 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.6748 0.10576 0.10124 0.0267 1.0000 0.0709
-8.250 -0.6803 0.10137 0.09690 0.0182 1.0000 0.0717
-8.000 -0.6831 0.09696 0.09237 0.0089 1.0000 0.0722
-7.750 -0.6688 0.09171 0.08728 0.0183 1.0000 0.0763
-7.500 -0.6622 0.08755 0.08311 0.0160 1.0000 0.0800
-7.250 -0.6569 0.08263 0.07811 0.0092 1.0000 0.0842
-7.000 -0.6536 0.07769 0.07282 -0.0001 1.0000 0.0870
-6.750 -0.6401 0.07275 0.06812 0.0034 1.0000 0.0902
-6.500 -0.6271 0.06881 0.06409 0.0017 1.0000 0.0960
-6.250 -0.6143 0.06381 0.05882 -0.0026 1.0000 0.1026
-6.000 -0.5984 0.06022 0.05524 -0.0024 1.0000 0.1093
-5.750 -0.5821 0.05596 0.05076 -0.0044 1.0000 0.1188
-5.500 -0.5641 0.05227 0.04687 -0.0059 1.0000 0.1318
-5.250 -0.5454 0.04885 0.04334 -0.0065 1.0000 0.1467
-5.000 -0.5258 0.04579 0.04020 -0.0068 1.0000 0.1652
-4.750 -0.5071 0.04291 0.03726 -0.0069 1.0000 0.1939
-4.250 -0.4745 0.03882 0.03315 -0.0048 1.0000 0.2979
-4.000 -0.4588 0.03556 0.03013 -0.0025 1.0000 0.3419
-3.750 -0.3689 0.02758 0.01896 -0.0090 1.0000 0.0852
-3.500 -0.3395 0.02432 0.01536 -0.0087 1.0000 0.0766
-3.250 -0.3086 0.02287 0.01335 -0.0080 1.0000 0.0730
-3.000 -0.2815 0.02063 0.01112 -0.0080 1.0000 0.0779
-2.750 -0.2528 0.01904 0.00937 -0.0075 1.0000 0.0788
-2.500 -0.2249 0.01766 0.00789 -0.0070 1.0000 0.0812
-2.250 -0.1975 0.01663 0.00679 -0.0064 1.0000 0.0865
-2.000 -0.1722 0.01537 0.00570 -0.0059 1.0000 0.0991
-1.750 -0.1466 0.01431 0.00471 -0.0054 1.0000 0.1143
-1.500 -0.0860 0.01069 0.00412 -0.0070 1.0000 1.0000
-1.250 -0.0620 0.01058 0.00375 -0.0066 1.0000 1.0000
-1.000 -0.0390 0.01050 0.00351 -0.0061 1.0000 1.0000
-0.750 -0.0171 0.01044 0.00333 -0.0053 1.0000 1.0000
-0.500 0.0030 0.01042 0.00321 -0.0043 1.0000 1.0000
-0.250 0.0209 0.01042 0.00313 -0.0028 1.0000 1.0000
0.000 0.0373 0.01045 0.00311 -0.0011 1.0000 1.0000
0.250 0.0543 0.01052 0.00313 0.0005 1.0000 1.0000
0.500 0.0733 0.01061 0.00319 0.0016 1.0000 1.0000
0.750 0.0936 0.01073 0.00329 0.0024 1.0000 1.0000
1.000 0.1151 0.01089 0.00344 0.0030 1.0000 1.0000
1.250 0.1373 0.01108 0.00365 0.0033 1.0000 1.0000
1.500 0.1599 0.01131 0.00391 0.0034 1.0000 1.0000
1.750 0.1953 0.01158 0.00426 0.0011 0.9949 1.0000
2.000 0.2710 0.01172 0.00460 -0.0085 0.9727 1.0000
2.250 0.3286 0.01179 0.00486 -0.0137 0.9415 1.0000
2.500 0.3606 0.01182 0.00502 -0.0131 0.9041 1.0000
2.750 0.3793 0.01176 0.00506 -0.0097 0.8609 1.0000
3.000 0.3959 0.01164 0.00495 -0.0057 0.8090 1.0000
3.250 0.4124 0.01159 0.00481 -0.0016 0.7398 1.0000
3.500 0.4303 0.01183 0.00473 0.0019 0.6432 1.0000
3.750 0.4515 0.01244 0.00486 0.0040 0.5417 1.0000
4.000 0.4755 0.01323 0.00527 0.0050 0.4623 1.0000
4.250 0.5004 0.01409 0.00580 0.0055 0.4003 1.0000
4.500 0.5258 0.01492 0.00640 0.0058 0.3440 1.0000
4.750 0.5516 0.01557 0.00688 0.0059 0.2863 1.0000
5.000 0.5777 0.01620 0.00741 0.0058 0.2248 1.0000
5.250 0.6023 0.01769 0.00844 0.0058 0.1348 1.0000
5.500 0.6267 0.01966 0.01006 0.0062 0.0905 1.0000
5.750 0.6525 0.02136 0.01180 0.0067 0.0745 1.0000
6.000 0.6777 0.02335 0.01373 0.0071 0.0649 1.0000
6.250 0.7047 0.02550 0.01621 0.0078 0.0606 1.0000
6.500 0.7309 0.02786 0.01889 0.0082 0.0572 1.0000
6.750 0.7540 0.03116 0.02240 0.0083 0.0530 1.0000
7.000 0.7777 0.03440 0.02628 0.0088 0.0521 1.0000
7.250 0.7981 0.03877 0.03120 0.0090 0.0526 1.0000
7.500 0.8165 0.04367 0.03651 0.0091 0.0538 1.0000
7.750 0.8232 0.05196 0.04614 0.0085 0.0626 1.0000
8.000 0.7819 0.04421 0.03887 0.0126 0.0669 1.0000
8.250 0.7838 0.08565 0.08114 -0.0162 0.1372 1.0000
8.500 0.7870 0.09029 0.08576 -0.0181 0.1347 1.0000
8.750 0.8093 0.09365 0.08917 -0.0117 0.1326 1.0000
9.000 0.7696 0.10154 0.09689 -0.0280 0.1274 1.0000
9.250 0.7686 0.10604 0.10135 -0.0304 0.1233 1.0000
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Polar data table (+)
Polar graphs
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