ONERA OA206 AIRFOIL (oa206-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: ONERA OA206 AIRFOIL (oa206-il) Reynolds number: 1,000,000 Max Cl/Cd: 69.7 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-oa206-il-1000000-n5.txt Download as CSV file: xf-oa206-il-1000000-n5.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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.7296 0.09653 0.09510 0.0383 1.0000 0.0048
-8.500 -0.7295 0.09195 0.09054 0.0350 1.0000 0.0048
-8.250 -0.7324 0.08655 0.08516 0.0297 1.0000 0.0049
-8.000 -0.7303 0.08017 0.07875 0.0220 1.0000 0.0049
-7.750 -0.7243 0.07395 0.07248 0.0162 1.0000 0.0050
-7.500 -0.7164 0.06742 0.06586 0.0112 1.0000 0.0051
-6.500 -0.6836 0.01755 0.01334 0.0023 1.0000 0.0065
-6.250 -0.6567 0.01577 0.01126 0.0020 0.9850 0.0067
-5.750 -0.6056 0.01295 0.00796 0.0026 0.9663 0.0072
-5.500 -0.5804 0.01248 0.00740 0.0031 0.9599 0.0076
-5.250 -0.5539 0.01206 0.00692 0.0033 0.9546 0.0079
-5.000 -0.5280 0.01159 0.00637 0.0037 0.9495 0.0082
-4.750 -0.5017 0.01112 0.00582 0.0040 0.9449 0.0087
-4.500 -0.4747 0.01065 0.00529 0.0041 0.9402 0.0091
-4.250 -0.4482 0.01023 0.00478 0.0044 0.9355 0.0095
-4.000 -0.4213 0.00985 0.00434 0.0047 0.9300 0.0099
-3.750 -0.3947 0.00953 0.00396 0.0050 0.9224 0.0102
-3.500 -0.3676 0.00913 0.00350 0.0052 0.9149 0.0105
-3.250 -0.3405 0.00870 0.00300 0.0053 0.9075 0.0115
-3.000 -0.3128 0.00850 0.00279 0.0054 0.8997 0.0126
-2.750 -0.2854 0.00831 0.00256 0.0056 0.8911 0.0136
-2.500 -0.2574 0.00810 0.00232 0.0056 0.8807 0.0145
-2.250 -0.2297 0.00794 0.00211 0.0057 0.8679 0.0151
-2.000 -0.2019 0.00772 0.00181 0.0058 0.8516 0.0169
-1.750 -0.1739 0.00758 0.00163 0.0058 0.8346 0.0193
-1.500 -0.1457 0.00749 0.00150 0.0058 0.8168 0.0219
-1.250 -0.1174 0.00739 0.00135 0.0058 0.7967 0.0260
-1.000 -0.0889 0.00732 0.00122 0.0057 0.7732 0.0317
-0.750 -0.0603 0.00728 0.00113 0.0055 0.7457 0.0427
-0.500 -0.0315 0.00721 0.00104 0.0053 0.7119 0.0713
-0.250 -0.0022 0.00694 0.00095 0.0047 0.6687 0.1797
0.000 0.0281 0.00597 0.00084 0.0032 0.6170 0.5115
0.250 0.0564 0.00513 0.00087 0.0026 0.5545 0.8232
0.500 0.0820 0.00527 0.00097 0.0033 0.4886 0.8866
1.000 0.1338 0.00570 0.00110 0.0043 0.3829 0.9280
1.250 0.1627 0.00585 0.00113 0.0040 0.3547 0.9321
1.500 0.1904 0.00596 0.00116 0.0040 0.3318 0.9356
1.750 0.2182 0.00607 0.00120 0.0041 0.3115 0.9395
2.000 0.2464 0.00617 0.00124 0.0040 0.2940 0.9433
2.250 0.2748 0.00631 0.00129 0.0038 0.2712 0.9468
2.500 0.3020 0.00641 0.00134 0.0040 0.2528 0.9503
2.750 0.3296 0.00655 0.00141 0.0040 0.2297 0.9540
3.000 0.3577 0.00673 0.00151 0.0038 0.2036 0.9576
3.250 0.3855 0.00704 0.00163 0.0037 0.1588 0.9610
3.500 0.4125 0.00725 0.00174 0.0037 0.1319 0.9649
3.750 0.4399 0.00747 0.00187 0.0037 0.1070 0.9692
4.250 0.4956 0.00800 0.00221 0.0034 0.0586 0.9788
4.500 0.5243 0.00833 0.00244 0.0031 0.0358 0.9848
4.750 0.5542 0.00865 0.00269 0.0024 0.0227 0.9942
5.000 0.5835 0.00892 0.00296 0.0019 0.0170 1.0000
5.250 0.6124 0.00920 0.00324 0.0016 0.0137 1.0000
5.500 0.6412 0.00949 0.00353 0.0012 0.0118 1.0000
5.750 0.6698 0.00986 0.00392 0.0008 0.0098 1.0000
6.000 0.6983 0.01016 0.00427 0.0005 0.0089 1.0000
6.250 0.7267 0.01048 0.00461 0.0002 0.0081 1.0000
6.500 0.7549 0.01083 0.00500 -0.0001 0.0074 1.0000
6.750 0.7829 0.01127 0.00546 -0.0004 0.0067 1.0000
7.000 0.8105 0.01193 0.00621 -0.0006 0.0060 1.0000
7.250 0.8382 0.01235 0.00671 -0.0008 0.0058 1.0000
7.500 0.8656 0.01283 0.00726 -0.0010 0.0056 1.0000
7.750 0.8928 0.01337 0.00787 -0.0012 0.0053 1.0000
8.000 0.9197 0.01396 0.00854 -0.0014 0.0050 1.0000
8.250 0.9463 0.01458 0.00924 -0.0015 0.0047 1.0000
8.500 0.9726 0.01522 0.00996 -0.0016 0.0045 1.0000
8.750 0.9986 0.01592 0.01077 -0.0017 0.0043 1.0000
9.000 1.0241 0.01669 0.01163 -0.0018 0.0041 1.0000
9.250 1.0481 0.01789 0.01298 -0.0017 0.0038 1.0000
9.500 1.0705 0.01945 0.01476 -0.0016 0.0036 1.0000
9.750 1.0942 0.02047 0.01592 -0.0015 0.0035 1.0000
10.000 1.1167 0.02172 0.01734 -0.0014 0.0035 1.0000
10.250 1.1380 0.02315 0.01897 -0.0012 0.0034 1.0000
10.500 1.1579 0.02476 0.02081 -0.0009 0.0034 1.0000
10.750 1.1760 0.02662 0.02290 -0.0006 0.0033 1.0000
11.000 1.1918 0.02875 0.02528 -0.0002 0.0033 1.0000
11.250 1.2043 0.03123 0.02803 0.0002 0.0032 1.0000
11.500 1.2125 0.03415 0.03125 0.0007 0.0032 1.0000
11.750 1.2149 0.03755 0.03493 0.0011 0.0031 1.0000
12.000 1.2081 0.04156 0.03923 0.0013 0.0031 1.0000
12.250 1.1900 0.04624 0.04413 0.0002 0.0031 1.0000
12.500 1.1682 0.05461 0.05273 -0.0075 0.0031 1.0000
12.750 1.1303 0.07330 0.07168 -0.0244 0.0032 1.0000
13.000 1.0743 0.09112 0.08959 -0.0346 0.0033 1.0000
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Polar data table (+)
Polar graphs
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