ONERA OA209 AIRFOIL (oa209-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: ONERA OA209 AIRFOIL (oa209-il) Reynolds number: 100,000 Max Cl/Cd: 41.46 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-oa209-il-100000-n5.txt Download as CSV file: xf-oa209-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.5855 0.08399 0.07939 -0.0048 1.0000 0.0518
-7.500 -0.5906 0.06892 0.06375 -0.0162 1.0000 0.0369
-7.250 -0.5807 0.06495 0.05975 -0.0168 1.0000 0.0363
-7.000 -0.5708 0.06075 0.05540 -0.0178 1.0000 0.0359
-6.750 -0.5591 0.05660 0.05106 -0.0186 1.0000 0.0353
-6.250 -0.5314 0.04569 0.03905 -0.0190 1.0000 0.0302
-6.000 -0.5133 0.04242 0.03557 -0.0189 1.0000 0.0299
-5.750 -0.4943 0.03925 0.03209 -0.0186 1.0000 0.0297
-5.500 -0.4743 0.03621 0.02870 -0.0180 1.0000 0.0296
-5.250 -0.4537 0.03341 0.02549 -0.0172 1.0000 0.0296
-5.000 -0.4327 0.03091 0.02250 -0.0161 1.0000 0.0304
-4.750 -0.4131 0.02946 0.02104 -0.0154 1.0000 0.0318
-4.500 -0.3929 0.02797 0.01936 -0.0143 1.0000 0.0332
-4.250 -0.3717 0.02622 0.01732 -0.0131 1.0000 0.0338
-4.000 -0.3499 0.02462 0.01545 -0.0118 1.0000 0.0344
-3.750 -0.3277 0.02319 0.01379 -0.0106 1.0000 0.0353
-3.500 -0.3051 0.02205 0.01240 -0.0094 1.0000 0.0369
-3.250 -0.2834 0.02101 0.01138 -0.0085 1.0000 0.0392
-3.000 -0.2613 0.02017 0.01052 -0.0076 1.0000 0.0414
-2.750 -0.2272 0.01913 0.00942 -0.0088 0.9959 0.0438
-2.500 -0.1878 0.01814 0.00846 -0.0112 0.9897 0.0483
-2.250 -0.1437 0.01733 0.00766 -0.0146 0.9825 0.0544
-2.000 -0.0994 0.01659 0.00691 -0.0180 0.9746 0.0640
-1.750 -0.0600 0.01601 0.00631 -0.0202 0.9649 0.0789
-1.500 -0.0254 0.01527 0.00583 -0.0215 0.9535 0.1305
-1.250 -0.0217 0.01304 0.00644 -0.0149 0.9414 0.8155
-1.000 -0.0044 0.01337 0.00675 -0.0103 0.9268 0.8989
-0.750 0.0307 0.01346 0.00676 -0.0093 0.9150 0.9553
-0.500 0.1126 0.01336 0.00645 -0.0189 0.9079 0.9886
-0.250 0.1454 0.01322 0.00621 -0.0198 0.8919 0.9947
0.000 0.1774 0.01306 0.00596 -0.0205 0.8737 1.0000
0.250 0.1974 0.01292 0.00575 -0.0188 0.8532 1.0000
0.500 0.2172 0.01277 0.00552 -0.0170 0.8313 1.0000
0.750 0.2369 0.01263 0.00530 -0.0150 0.8057 1.0000
1.000 0.2564 0.01250 0.00508 -0.0129 0.7763 1.0000
1.250 0.2755 0.01239 0.00483 -0.0107 0.7403 1.0000
1.500 0.2949 0.01235 0.00461 -0.0085 0.6942 1.0000
1.750 0.3145 0.01241 0.00440 -0.0063 0.6339 1.0000
2.000 0.3350 0.01264 0.00426 -0.0046 0.5629 1.0000
2.250 0.3568 0.01301 0.00423 -0.0033 0.4953 1.0000
2.500 0.3797 0.01341 0.00431 -0.0026 0.4459 1.0000
2.750 0.4035 0.01380 0.00446 -0.0020 0.4124 1.0000
3.000 0.4279 0.01416 0.00464 -0.0016 0.3871 1.0000
3.250 0.4530 0.01452 0.00485 -0.0012 0.3667 1.0000
3.500 0.4785 0.01487 0.00510 -0.0010 0.3489 1.0000
3.750 0.5045 0.01522 0.00538 -0.0009 0.3331 1.0000
4.000 0.5308 0.01558 0.00567 -0.0008 0.3185 1.0000
4.250 0.5573 0.01594 0.00598 -0.0007 0.3047 1.0000
4.500 0.5839 0.01632 0.00632 -0.0007 0.2920 1.0000
5.000 0.6375 0.01707 0.00704 -0.0008 0.2674 1.0000
5.250 0.6643 0.01746 0.00745 -0.0009 0.2557 1.0000
5.500 0.6911 0.01788 0.00788 -0.0009 0.2448 1.0000
5.750 0.7177 0.01832 0.00831 -0.0010 0.2342 1.0000
6.000 0.7446 0.01874 0.00880 -0.0011 0.2230 1.0000
6.250 0.7711 0.01921 0.00932 -0.0011 0.2129 1.0000
6.500 0.7973 0.01971 0.00981 -0.0012 0.2033 1.0000
6.750 0.8238 0.02018 0.01040 -0.0012 0.1924 1.0000
7.000 0.8498 0.02072 0.01101 -0.0012 0.1825 1.0000
7.250 0.8753 0.02125 0.01155 -0.0013 0.1727 1.0000
7.500 0.9010 0.02177 0.01219 -0.0013 0.1616 1.0000
7.750 0.9263 0.02234 0.01287 -0.0013 0.1504 1.0000
8.000 0.9510 0.02294 0.01355 -0.0012 0.1396 1.0000
8.250 0.9752 0.02358 0.01424 -0.0012 0.1291 1.0000
8.500 0.9990 0.02428 0.01501 -0.0011 0.1184 1.0000
8.750 1.0225 0.02504 0.01593 -0.0009 0.1075 1.0000
9.000 1.0452 0.02591 0.01692 -0.0007 0.0973 1.0000
9.250 1.0666 0.02690 0.01799 -0.0004 0.0881 1.0000
9.500 1.0866 0.02800 0.01913 -0.0001 0.0800 1.0000
9.750 1.1068 0.02916 0.02048 0.0003 0.0722 1.0000
10.000 1.1245 0.03053 0.02192 0.0009 0.0667 1.0000
10.250 1.1419 0.03190 0.02346 0.0015 0.0615 1.0000
10.500 1.1565 0.03342 0.02503 0.0023 0.0577 1.0000
10.750 1.1712 0.03504 0.02692 0.0031 0.0540 1.0000
11.000 1.1836 0.03670 0.02872 0.0040 0.0514 1.0000
11.250 1.1932 0.03849 0.03056 0.0050 0.0493 1.0000
11.500 1.2012 0.04054 0.03287 0.0061 0.0473 1.0000
11.750 1.2051 0.04264 0.03521 0.0075 0.0454 1.0000
12.000 1.2064 0.04487 0.03762 0.0087 0.0439 1.0000
12.250 1.2067 0.04729 0.04020 0.0095 0.0427 1.0000
12.500 1.2058 0.04998 0.04302 0.0100 0.0418 1.0000
12.750 1.2039 0.05297 0.04611 0.0100 0.0410 1.0000
13.000 1.1982 0.05666 0.04997 0.0095 0.0404 1.0000
13.250 1.1872 0.06135 0.05495 0.0079 0.0399 1.0000
13.500 1.1730 0.06693 0.06080 0.0051 0.0395 1.0000
13.750 1.1553 0.07365 0.06778 0.0010 0.0393 1.0000
14.000 1.1335 0.08173 0.07610 -0.0044 0.0392 1.0000
14.250 1.1065 0.09140 0.08599 -0.0110 0.0393 1.0000
14.500 1.0724 0.10300 0.09778 -0.0185 0.0397 1.0000
14.750 1.0278 0.11747 0.11238 -0.0275 0.0402 1.0000
15.000 0.9459 0.14369 0.13866 -0.0423 0.0407 1.0000
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Polar data table (+)
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