ONERA OA209 AIRFOIL (oa209-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: ONERA OA209 AIRFOIL (oa209-il) Reynolds number: 100,000 Max Cl/Cd: 35.97 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-oa209-il-100000.txt Download as CSV file: xf-oa209-il-100000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5997 0.10210 0.09753 0.0024 1.0000 0.0831
-8.500 -0.6164 0.09748 0.09284 -0.0064 1.0000 0.0836
-8.250 -0.6289 0.09420 0.08932 -0.0116 1.0000 0.0840
-8.000 -0.5885 0.08787 0.08339 -0.0021 1.0000 0.0880
-7.750 -0.5829 0.08397 0.07947 -0.0037 1.0000 0.0910
-7.500 -0.5816 0.07940 0.07484 -0.0081 1.0000 0.0951
-7.000 -0.5745 0.06992 0.06518 -0.0144 1.0000 0.1030
-6.750 -0.5620 0.06666 0.06187 -0.0150 1.0000 0.1102
-6.500 -0.5555 0.06217 0.05715 -0.0177 1.0000 0.1180
-6.250 -0.5399 0.05915 0.05411 -0.0177 1.0000 0.1268
-6.000 -0.4924 0.04231 0.03734 -0.0211 1.0000 0.1476
-5.750 -0.4773 0.03849 0.03378 -0.0195 1.0000 0.1533
-5.500 -0.4995 0.04906 0.04362 -0.0191 1.0000 0.1662
-5.250 -0.4846 0.04628 0.04086 -0.0184 1.0000 0.1840
-5.000 -0.4725 0.04397 0.03850 -0.0175 1.0000 0.2132
-4.500 -0.4496 0.03967 0.03434 -0.0134 1.0000 0.2759
-4.250 -0.4392 0.03780 0.03266 -0.0101 1.0000 0.3139
-4.000 -0.4310 0.03599 0.03105 -0.0061 1.0000 0.3611
-3.750 -0.3435 0.02834 0.02012 -0.0133 1.0000 0.0935
-3.500 -0.3176 0.02644 0.01768 -0.0115 1.0000 0.0816
-3.250 -0.2942 0.02442 0.01545 -0.0104 1.0000 0.0787
-3.000 -0.2705 0.02300 0.01382 -0.0092 1.0000 0.0791
-2.750 -0.2466 0.02190 0.01252 -0.0081 1.0000 0.0813
-2.500 -0.2222 0.02076 0.01126 -0.0071 1.0000 0.0823
-2.250 -0.1977 0.01976 0.01018 -0.0061 1.0000 0.0845
-2.000 -0.1739 0.01849 0.00911 -0.0056 1.0000 0.0918
-1.750 -0.1497 0.01778 0.00839 -0.0048 1.0000 0.0983
-1.500 -0.1254 0.01688 0.00765 -0.0044 1.0000 0.1113
-1.250 -0.0993 0.01611 0.00696 -0.0043 1.0000 0.1350
-1.000 -0.0169 0.01373 0.00745 -0.0074 1.0000 1.0000
-0.750 -0.0156 0.01374 0.00736 -0.0036 1.0000 1.0000
-0.500 -0.0130 0.01377 0.00730 -0.0001 1.0000 1.0000
-0.250 -0.0045 0.01385 0.00729 0.0023 0.9995 1.0000
0.000 0.0583 0.01409 0.00736 -0.0049 0.9881 1.0000
0.250 0.1265 0.01428 0.00743 -0.0130 0.9764 1.0000
0.500 0.2006 0.01432 0.00740 -0.0220 0.9643 1.0000
0.750 0.2566 0.01430 0.00736 -0.0271 0.9453 1.0000
1.000 0.2972 0.01423 0.00730 -0.0287 0.9228 1.0000
1.250 0.3203 0.01408 0.00716 -0.0266 0.8965 1.0000
1.500 0.3366 0.01381 0.00689 -0.0231 0.8674 1.0000
1.750 0.3512 0.01343 0.00650 -0.0190 0.8355 1.0000
2.000 0.3654 0.01304 0.00607 -0.0149 0.7953 1.0000
2.250 0.3792 0.01270 0.00558 -0.0104 0.7408 1.0000
2.500 0.3941 0.01264 0.00516 -0.0063 0.6600 1.0000
2.750 0.4128 0.01302 0.00501 -0.0037 0.5736 1.0000
3.000 0.4349 0.01359 0.00512 -0.0024 0.5149 1.0000
3.250 0.4589 0.01416 0.00537 -0.0017 0.4753 1.0000
3.500 0.4839 0.01473 0.00569 -0.0012 0.4453 1.0000
3.750 0.5093 0.01534 0.00609 -0.0009 0.4214 1.0000
4.000 0.5354 0.01592 0.00655 -0.0007 0.3994 1.0000
4.250 0.5618 0.01654 0.00703 -0.0006 0.3803 1.0000
4.500 0.5884 0.01717 0.00758 -0.0006 0.3628 1.0000
4.750 0.6152 0.01781 0.00815 -0.0006 0.3465 1.0000
5.000 0.6421 0.01845 0.00876 -0.0006 0.3309 1.0000
5.250 0.6691 0.01910 0.00941 -0.0007 0.3161 1.0000
5.500 0.6961 0.01978 0.01013 -0.0007 0.3022 1.0000
5.750 0.7230 0.02046 0.01083 -0.0008 0.2888 1.0000
6.000 0.7499 0.02118 0.01153 -0.0008 0.2764 1.0000
6.250 0.7766 0.02188 0.01219 -0.0008 0.2645 1.0000
6.500 0.8032 0.02252 0.01299 -0.0009 0.2515 1.0000
6.750 0.8296 0.02329 0.01388 -0.0009 0.2392 1.0000
7.000 0.8557 0.02403 0.01470 -0.0009 0.2272 1.0000
7.250 0.8816 0.02472 0.01538 -0.0009 0.2156 1.0000
7.500 0.9073 0.02533 0.01594 -0.0008 0.2034 1.0000
7.750 0.9323 0.02592 0.01670 -0.0007 0.1902 1.0000
8.000 0.9567 0.02661 0.01754 -0.0005 0.1769 1.0000
8.250 0.9807 0.02738 0.01843 -0.0003 0.1637 1.0000
8.500 1.0040 0.02822 0.01936 -0.0001 0.1504 1.0000
8.750 1.0266 0.02920 0.02044 0.0003 0.1373 1.0000
9.000 1.0485 0.03039 0.02173 0.0007 0.1253 1.0000
9.250 1.0701 0.03169 0.02304 0.0011 0.1147 1.0000
9.500 1.0918 0.03296 0.02430 0.0015 0.1057 1.0000
9.750 1.1094 0.03517 0.02695 0.0022 0.0981 1.0000
10.000 1.1309 0.03686 0.02846 0.0024 0.0918 1.0000
10.250 1.1433 0.03951 0.03175 0.0036 0.0871 1.0000
10.500 1.1589 0.04173 0.03418 0.0043 0.0831 1.0000
10.750 1.1752 0.04446 0.03692 0.0047 0.0796 1.0000
11.000 1.1743 0.04808 0.04121 0.0063 0.0774 1.0000
11.250 1.1697 0.05204 0.04566 0.0076 0.0756 1.0000
11.500 1.1583 0.05641 0.05044 0.0088 0.0746 1.0000
11.750 1.1346 0.06118 0.05556 0.0101 0.0745 1.0000
12.000 1.0990 0.06742 0.06210 0.0093 0.0752 1.0000
12.250 1.0530 0.07675 0.07167 0.0039 0.0767 1.0000
12.500 1.0076 0.08912 0.08417 -0.0050 0.0788 1.0000
12.750 0.9727 0.10177 0.09685 -0.0130 0.0801 1.0000
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Polar data table (+)
Polar graphs
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