ONERA OA209 AIRFOIL (oa209-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: ONERA OA209 AIRFOIL (oa209-il) Reynolds number: 50,000 Max Cl/Cd: 28.64 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-oa209-il-50000-n5.txt Download as CSV file: xf-oa209-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: ONERA OA209 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.5890 0.12967 0.12285 0.0218 1.0000 0.1080
-10.000 -0.5911 0.12622 0.11945 0.0187 1.0000 0.1125
-9.750 -0.6098 0.12352 0.11686 0.0112 1.0000 0.1149
-9.500 -0.5933 0.11797 0.11133 0.0130 1.0000 0.1169
-9.250 -0.5803 0.11384 0.10720 0.0138 1.0000 0.1201
-9.000 -0.5759 0.10999 0.10337 0.0123 1.0000 0.1238
-8.750 -0.6015 0.10637 0.09988 0.0024 1.0000 0.1306
-8.500 -0.5879 0.10145 0.09500 0.0038 1.0000 0.1330
-8.250 -0.5762 0.09747 0.09102 0.0044 1.0000 0.1362
-8.000 -0.5748 0.09329 0.08688 0.0017 1.0000 0.1396
-7.500 -0.5743 0.07684 0.07005 -0.0137 1.0000 0.0643
-7.250 -0.5748 0.07063 0.06340 -0.0177 1.0000 0.0558
-7.000 -0.5647 0.06650 0.05918 -0.0183 1.0000 0.0549
-6.750 -0.5544 0.06244 0.05492 -0.0191 1.0000 0.0545
-6.500 -0.5423 0.05853 0.05073 -0.0196 1.0000 0.0544
-6.250 -0.5282 0.05481 0.04672 -0.0200 1.0000 0.0543
-6.000 -0.5123 0.05125 0.04285 -0.0200 1.0000 0.0540
-5.750 -0.4948 0.04783 0.03911 -0.0199 1.0000 0.0533
-5.500 -0.4758 0.04461 0.03553 -0.0196 1.0000 0.0526
-5.250 -0.4556 0.04164 0.03216 -0.0191 1.0000 0.0522
-5.000 -0.4344 0.03893 0.02903 -0.0184 1.0000 0.0521
-4.750 -0.4125 0.03661 0.02632 -0.0176 1.0000 0.0533
-4.500 -0.3900 0.03460 0.02386 -0.0167 1.0000 0.0553
-4.250 -0.3670 0.03279 0.02161 -0.0155 1.0000 0.0566
-4.000 -0.3446 0.03079 0.01941 -0.0145 1.0000 0.0574
-3.750 -0.3223 0.02904 0.01754 -0.0134 1.0000 0.0589
-3.500 -0.3000 0.02770 0.01614 -0.0124 1.0000 0.0622
-3.250 -0.2769 0.02654 0.01483 -0.0112 1.0000 0.0662
-3.000 -0.2531 0.02547 0.01358 -0.0098 1.0000 0.0690
-2.750 -0.2303 0.02432 0.01246 -0.0085 1.0000 0.0734
-2.500 -0.2080 0.02351 0.01158 -0.0074 1.0000 0.0803
-2.250 -0.1865 0.02267 0.01066 -0.0061 1.0000 0.0863
-2.000 -0.1656 0.02195 0.00990 -0.0050 1.0000 0.0973
-1.750 -0.1442 0.02119 0.00914 -0.0041 1.0000 0.1121
-1.250 -0.0202 0.01775 0.00876 -0.0110 1.0000 1.0000
-1.000 -0.0141 0.01773 0.00859 -0.0079 1.0000 1.0000
-0.750 -0.0078 0.01775 0.00847 -0.0048 1.0000 1.0000
-0.500 -0.0010 0.01778 0.00838 -0.0019 1.0000 1.0000
-0.250 0.0505 0.01796 0.00831 -0.0071 0.9859 1.0000
0.000 0.1048 0.01810 0.00828 -0.0127 0.9710 1.0000
0.250 0.1574 0.01823 0.00828 -0.0177 0.9549 1.0000
0.500 0.2015 0.01833 0.00831 -0.0209 0.9356 1.0000
0.750 0.2371 0.01838 0.00833 -0.0221 0.9127 1.0000
1.000 0.2646 0.01837 0.00830 -0.0217 0.8867 1.0000
1.250 0.2894 0.01829 0.00821 -0.0205 0.8583 1.0000
1.500 0.3122 0.01816 0.00807 -0.0188 0.8270 1.0000
1.750 0.3343 0.01801 0.00790 -0.0168 0.7912 1.0000
2.000 0.3559 0.01786 0.00770 -0.0145 0.7497 1.0000
2.250 0.3771 0.01776 0.00747 -0.0121 0.6997 1.0000
2.500 0.3977 0.01777 0.00724 -0.0094 0.6411 1.0000
2.750 0.4181 0.01797 0.00711 -0.0070 0.5800 1.0000
3.000 0.4392 0.01838 0.00715 -0.0052 0.5257 1.0000
3.250 0.4613 0.01890 0.00734 -0.0040 0.4839 1.0000
3.500 0.4844 0.01946 0.00765 -0.0031 0.4510 1.0000
3.750 0.5081 0.02005 0.00806 -0.0024 0.4249 1.0000
4.000 0.5325 0.02064 0.00852 -0.0019 0.4021 1.0000
4.250 0.5576 0.02126 0.00904 -0.0016 0.3821 1.0000
4.500 0.5830 0.02188 0.00962 -0.0013 0.3641 1.0000
4.750 0.6087 0.02252 0.01022 -0.0010 0.3474 1.0000
5.000 0.6346 0.02317 0.01087 -0.0008 0.3319 1.0000
5.250 0.6604 0.02383 0.01156 -0.0006 0.3168 1.0000
5.500 0.6863 0.02453 0.01233 -0.0004 0.3030 1.0000
5.750 0.7120 0.02524 0.01309 -0.0002 0.2896 1.0000
6.000 0.7375 0.02598 0.01386 -0.0001 0.2773 1.0000
6.250 0.7629 0.02673 0.01469 0.0001 0.2650 1.0000
6.500 0.7882 0.02754 0.01567 0.0003 0.2523 1.0000
6.750 0.8131 0.02841 0.01669 0.0004 0.2406 1.0000
7.000 0.8377 0.02926 0.01763 0.0006 0.2293 1.0000
7.250 0.8621 0.03010 0.01855 0.0009 0.2187 1.0000
7.500 0.8857 0.03109 0.01977 0.0011 0.2064 1.0000
7.750 0.9088 0.03214 0.02103 0.0014 0.1950 1.0000
8.000 0.9313 0.03310 0.02215 0.0017 0.1836 1.0000
8.250 0.9535 0.03396 0.02304 0.0021 0.1729 1.0000
8.500 0.9742 0.03505 0.02436 0.0025 0.1608 1.0000
8.750 0.9937 0.03631 0.02588 0.0030 0.1489 1.0000
9.000 1.0124 0.03769 0.02749 0.0035 0.1380 1.0000
9.250 1.0304 0.03896 0.02887 0.0040 0.1281 1.0000
9.500 1.0475 0.04032 0.03034 0.0046 0.1189 1.0000
9.750 1.0607 0.04250 0.03288 0.0053 0.1100 1.0000
10.000 1.0757 0.04407 0.03449 0.0060 0.1034 1.0000
10.250 1.0838 0.04677 0.03761 0.0068 0.0965 1.0000
10.500 1.0974 0.04830 0.03909 0.0076 0.0916 1.0000
10.750 1.0949 0.05228 0.04364 0.0084 0.0875 1.0000
11.000 1.0944 0.05537 0.04700 0.0091 0.0839 1.0000
11.250 1.1046 0.05685 0.04841 0.0099 0.0804 1.0000
11.500 1.0884 0.06119 0.05307 0.0106 0.0789 1.0000
11.750 1.0636 0.06695 0.05916 0.0094 0.0782 1.0000
12.000 1.0327 0.07454 0.06701 0.0056 0.0782 1.0000
12.250 0.9944 0.08514 0.07778 -0.0015 0.0789 1.0000
12.500 0.9492 0.09953 0.09226 -0.0114 0.0797 1.0000
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Polar data table (+)
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