ONERA OA209 AIRFOIL (oa209-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: ONERA OA209 AIRFOIL (oa209-il) Reynolds number: 50,000 Max Cl/Cd: 25.82 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-oa209-il-50000.txt Download as CSV file: xf-oa209-il-50000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5555 0.10479 0.09841 0.0236 1.0000 0.2809
-8.000 -0.5570 0.10196 0.09565 0.0234 1.0000 0.3016
-7.750 -0.5708 0.09971 0.09351 0.0221 1.0000 0.3199
-7.500 -0.5560 0.09633 0.09015 0.0250 1.0000 0.3516
-7.250 -0.5215 0.09202 0.08581 0.0296 1.0000 0.3921
-7.000 -0.5187 0.08970 0.08355 0.0320 1.0000 0.4303
-6.750 -0.4961 0.08641 0.08027 0.0356 1.0000 0.4767
-6.500 -0.4883 0.08436 0.07827 0.0395 1.0000 0.5266
-6.250 -0.4510 0.08056 0.07443 0.0431 1.0000 0.5889
-6.000 -0.4253 0.07768 0.07156 0.0465 1.0000 0.6533
-5.000 -0.4812 0.04799 0.04073 -0.0152 1.0000 0.2558
-4.750 -0.4422 0.04230 0.03383 -0.0190 1.0000 0.1759
-4.500 -0.4161 0.03887 0.02990 -0.0187 1.0000 0.1561
-4.250 -0.3900 0.03648 0.02681 -0.0179 1.0000 0.1449
-4.000 -0.3668 0.03388 0.02394 -0.0170 1.0000 0.1408
-3.750 -0.3415 0.03172 0.02129 -0.0158 1.0000 0.1345
-3.500 -0.3157 0.03042 0.01941 -0.0144 1.0000 0.1308
-3.250 -0.2917 0.02834 0.01720 -0.0133 1.0000 0.1325
-3.000 -0.2678 0.02660 0.01546 -0.0123 1.0000 0.1371
-2.750 -0.2425 0.02524 0.01397 -0.0109 1.0000 0.1405
-2.500 -0.2169 0.02422 0.01276 -0.0095 1.0000 0.1469
-2.250 -0.1921 0.02291 0.01157 -0.0082 1.0000 0.1589
-2.000 -0.0451 0.01793 0.00974 -0.0197 1.0000 1.0000
-1.750 -0.0342 0.01785 0.00928 -0.0171 1.0000 1.0000
-1.500 -0.0267 0.01778 0.00899 -0.0141 1.0000 1.0000
-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 0.0075 0.01786 0.00834 0.0007 1.0000 1.0000
0.000 0.0190 0.01798 0.00834 0.0027 1.0000 1.0000
0.250 0.0332 0.01816 0.00842 0.0042 1.0000 1.0000
0.500 0.0493 0.01840 0.00857 0.0052 1.0000 1.0000
0.750 0.0668 0.01870 0.00882 0.0058 1.0000 1.0000
1.000 0.0850 0.01909 0.00916 0.0061 1.0000 1.0000
1.250 0.1034 0.01958 0.00963 0.0062 1.0000 1.0000
1.500 0.1247 0.02023 0.01029 0.0053 0.9984 1.0000
1.750 0.2338 0.02138 0.01154 -0.0108 0.9564 1.0000
2.000 0.3389 0.02163 0.01204 -0.0240 0.9021 1.0000
2.250 0.3972 0.02103 0.01160 -0.0264 0.8415 1.0000
2.500 0.4281 0.02020 0.01077 -0.0232 0.7838 1.0000
2.750 0.4479 0.01970 0.01011 -0.0185 0.7265 1.0000
3.000 0.4666 0.01961 0.00974 -0.0144 0.6744 1.0000
3.250 0.4868 0.01986 0.00969 -0.0114 0.6280 1.0000
3.500 0.5087 0.02039 0.01001 -0.0094 0.5873 1.0000
3.750 0.5321 0.02102 0.01041 -0.0080 0.5532 1.0000
4.000 0.5565 0.02177 0.01101 -0.0070 0.5233 1.0000
4.250 0.5813 0.02260 0.01172 -0.0062 0.4967 1.0000
4.500 0.6065 0.02349 0.01252 -0.0055 0.4733 1.0000
4.750 0.6319 0.02451 0.01350 -0.0050 0.4510 1.0000
5.000 0.6574 0.02561 0.01461 -0.0047 0.4305 1.0000
5.250 0.6828 0.02676 0.01575 -0.0044 0.4116 1.0000
5.500 0.7082 0.02803 0.01707 -0.0041 0.3942 1.0000
5.750 0.7333 0.02939 0.01847 -0.0038 0.3773 1.0000
6.000 0.7581 0.03087 0.02007 -0.0037 0.3614 1.0000
6.250 0.7824 0.03248 0.02183 -0.0035 0.3460 1.0000
6.500 0.8059 0.03421 0.02378 -0.0034 0.3309 1.0000
6.750 0.8283 0.03618 0.02601 -0.0034 0.3167 1.0000
7.000 0.8499 0.03819 0.02825 -0.0032 0.3024 1.0000
7.250 0.8705 0.04038 0.03067 -0.0030 0.2892 1.0000
7.500 0.8908 0.04243 0.03292 -0.0026 0.2753 1.0000
7.750 0.9111 0.04444 0.03507 -0.0020 0.2620 1.0000
8.000 0.9311 0.04631 0.03704 -0.0013 0.2477 1.0000
8.250 0.9492 0.04841 0.03933 -0.0007 0.2338 1.0000
8.500 0.9522 0.05288 0.04439 -0.0008 0.2225 1.0000
8.750 0.9570 0.05694 0.04876 -0.0007 0.2125 1.0000
9.000 0.9727 0.05919 0.05108 0.0002 0.2010 1.0000
9.250 0.9498 0.06708 0.05943 -0.0016 0.1988 1.0000
9.500 0.9212 0.07557 0.06812 -0.0047 0.1994 1.0000
9.750 0.8927 0.08399 0.07659 -0.0085 0.2012 1.0000
10.000 0.8699 0.09305 0.08562 -0.0139 0.2037 1.0000
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