ONERA OA209 AIRFOIL (oa209-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: ONERA OA209 AIRFOIL (oa209-il) Reynolds number: 1,000,000 Max Cl/Cd: 90.5 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-oa209-il-1000000.txt Download as CSV file: xf-oa209-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.6305 0.10642 0.10496 0.0265 1.0000 0.0112
-9.250 -0.6284 0.10167 0.10021 0.0235 1.0000 0.0115
-9.000 -0.6272 0.09651 0.09506 0.0198 1.0000 0.0119
-8.750 -0.5355 0.07003 0.06866 -0.0047 0.9909 0.0130
-8.500 -0.5517 0.06237 0.06096 -0.0124 0.9818 0.0129
-8.250 -0.5709 0.05783 0.05634 -0.0136 0.9726 0.0129
-8.000 -0.5947 0.05154 0.04993 -0.0137 0.9653 0.0130
-7.750 -0.5978 0.04708 0.04537 -0.0137 0.9607 0.0131
-7.500 -0.6495 0.05370 0.05166 -0.0102 0.9648 0.0131
-7.250 -0.6385 0.05077 0.04863 -0.0102 0.9609 0.0132
-7.000 -0.6256 0.04808 0.04582 -0.0100 0.9566 0.0134
-6.750 -0.6125 0.04556 0.04318 -0.0092 0.9525 0.0136
-6.500 -0.5955 0.04268 0.04016 -0.0091 0.9490 0.0139
-6.250 -0.5777 0.03963 0.03694 -0.0087 0.9451 0.0143
-6.000 -0.5702 0.02555 0.02183 -0.0055 0.9409 0.0125
-5.750 -0.5531 0.01819 0.01354 -0.0037 0.9376 0.0124
-5.500 -0.5274 0.01667 0.01176 -0.0032 0.9331 0.0127
-5.250 -0.5037 0.01524 0.01008 -0.0021 0.9281 0.0130
-5.000 -0.4801 0.01371 0.00840 -0.0012 0.9238 0.0134
-4.750 -0.4531 0.01304 0.00768 -0.0011 0.9189 0.0137
-4.500 -0.4271 0.01253 0.00713 -0.0005 0.9143 0.0142
-4.250 -0.4015 0.01211 0.00665 0.0001 0.9101 0.0148
-4.000 -0.3731 0.01164 0.00614 0.0001 0.9050 0.0155
-3.750 -0.3459 0.01128 0.00573 0.0004 0.8997 0.0160
-3.500 -0.3200 0.01042 0.00479 0.0009 0.8950 0.0168
-3.250 -0.2913 0.00999 0.00438 0.0008 0.8888 0.0175
-3.000 -0.2636 0.00967 0.00403 0.0009 0.8825 0.0184
-2.750 -0.2354 0.00936 0.00370 0.0010 0.8750 0.0194
-2.500 -0.2072 0.00901 0.00329 0.0011 0.8665 0.0205
-2.250 -0.1785 0.00869 0.00299 0.0010 0.8577 0.0223
-1.750 -0.1209 0.00821 0.00244 0.0009 0.8372 0.0263
-1.500 -0.0920 0.00804 0.00225 0.0008 0.8246 0.0293
-1.250 -0.0630 0.00786 0.00205 0.0007 0.8101 0.0344
-1.000 -0.0338 0.00771 0.00188 0.0005 0.7921 0.0431
-0.750 -0.0044 0.00755 0.00174 0.0003 0.7721 0.0673
-0.500 0.0261 0.00643 0.00153 -0.0011 0.7465 0.3746
-0.250 0.0568 0.00516 0.00142 -0.0025 0.7168 0.7419
0.000 0.0849 0.00509 0.00148 -0.0023 0.6773 0.8263
0.250 0.1134 0.00527 0.00154 -0.0022 0.6234 0.8593
0.500 0.1420 0.00559 0.00162 -0.0023 0.5526 0.8788
0.750 0.1708 0.00603 0.00173 -0.0026 0.4624 0.8929
1.000 0.1985 0.00639 0.00186 -0.0025 0.4031 0.9059
1.250 0.2245 0.00663 0.00198 -0.0018 0.3707 0.9174
1.500 0.2520 0.00677 0.00202 -0.0017 0.3480 0.9228
1.750 0.2801 0.00689 0.00206 -0.0017 0.3308 0.9269
2.000 0.3090 0.00701 0.00211 -0.0019 0.3153 0.9306
2.250 0.3382 0.00712 0.00215 -0.0022 0.3023 0.9339
2.500 0.3658 0.00719 0.00218 -0.0021 0.2901 0.9372
2.750 0.3937 0.00729 0.00222 -0.0021 0.2780 0.9408
3.000 0.4222 0.00739 0.00227 -0.0022 0.2672 0.9444
3.250 0.4510 0.00749 0.00233 -0.0024 0.2569 0.9476
3.500 0.4780 0.00756 0.00237 -0.0022 0.2461 0.9511
3.750 0.5055 0.00766 0.00243 -0.0021 0.2362 0.9548
4.000 0.5336 0.00776 0.00250 -0.0022 0.2269 0.9583
4.250 0.5616 0.00788 0.00258 -0.0023 0.2165 0.9617
4.500 0.5882 0.00795 0.00264 -0.0020 0.2075 0.9656
4.750 0.6156 0.00806 0.00273 -0.0019 0.1986 0.9696
5.000 0.6434 0.00822 0.00283 -0.0020 0.1881 0.9735
5.250 0.6707 0.00831 0.00292 -0.0019 0.1797 0.9780
5.500 0.6989 0.00846 0.00303 -0.0021 0.1686 0.9829
5.750 0.7288 0.00865 0.00317 -0.0027 0.1575 0.9878
6.250 0.7900 0.00904 0.00351 -0.0043 0.1389 1.0000
6.500 0.8198 0.00930 0.00372 -0.0050 0.1297 1.0000
6.750 0.8495 0.00955 0.00394 -0.0057 0.1211 1.0000
7.000 0.8790 0.00979 0.00417 -0.0063 0.1130 1.0000
7.250 0.9083 0.01009 0.00443 -0.0069 0.1040 1.0000
7.500 0.9375 0.01037 0.00469 -0.0074 0.0961 1.0000
7.750 0.9665 0.01068 0.00498 -0.0080 0.0874 1.0000
8.000 0.9951 0.01103 0.00529 -0.0085 0.0779 1.0000
8.250 1.0234 0.01144 0.00564 -0.0090 0.0678 1.0000
8.500 1.0513 0.01188 0.00604 -0.0094 0.0572 1.0000
8.750 1.0789 0.01239 0.00649 -0.0098 0.0473 1.0000
9.000 1.1061 0.01292 0.00699 -0.0102 0.0397 1.0000
9.250 1.1330 0.01347 0.00752 -0.0105 0.0346 1.0000
9.500 1.1601 0.01393 0.00801 -0.0107 0.0318 1.0000
9.750 1.1866 0.01447 0.00856 -0.0109 0.0292 1.0000
10.000 1.2124 0.01511 0.00924 -0.0110 0.0270 1.0000
10.250 1.2388 0.01555 0.00973 -0.0112 0.0257 1.0000
10.500 1.2645 0.01608 0.01030 -0.0113 0.0243 1.0000
10.750 1.2885 0.01688 0.01114 -0.0112 0.0226 1.0000
11.000 1.3128 0.01755 0.01189 -0.0112 0.0218 1.0000
11.250 1.3374 0.01809 0.01250 -0.0111 0.0211 1.0000
11.500 1.3613 0.01871 0.01318 -0.0110 0.0203 1.0000
11.750 1.3845 0.01936 0.01389 -0.0108 0.0196 1.0000
12.000 1.4060 0.02020 0.01478 -0.0105 0.0187 1.0000
12.250 1.4225 0.02160 0.01629 -0.0097 0.0178 1.0000
12.500 1.4442 0.02224 0.01701 -0.0094 0.0175 1.0000
12.750 1.4645 0.02300 0.01785 -0.0089 0.0171 1.0000
13.000 1.4833 0.02385 0.01879 -0.0082 0.0167 1.0000
13.250 1.5006 0.02477 0.01981 -0.0075 0.0162 1.0000
13.500 1.5163 0.02576 0.02087 -0.0066 0.0158 1.0000
13.750 1.5299 0.02681 0.02200 -0.0055 0.0154 1.0000
14.000 1.5370 0.02808 0.02335 -0.0038 0.0151 1.0000
14.250 1.5369 0.02987 0.02524 -0.0017 0.0147 1.0000
14.500 1.5292 0.03251 0.02802 0.0002 0.0143 1.0000
14.750 1.5236 0.03532 0.03097 0.0012 0.0141 1.0000
15.000 1.5266 0.03757 0.03334 0.0014 0.0140 1.0000
15.250 1.5270 0.04031 0.03620 0.0011 0.0139 1.0000
15.500 1.5241 0.04375 0.03978 0.0001 0.0138 1.0000
15.750 1.5180 0.04801 0.04418 -0.0018 0.0136 1.0000
16.000 1.5071 0.05349 0.04983 -0.0048 0.0135 1.0000
16.250 1.4913 0.06031 0.05681 -0.0089 0.0135 1.0000
16.500 1.4705 0.06839 0.06506 -0.0137 0.0134 1.0000
16.750 1.4452 0.07703 0.07385 -0.0184 0.0134 1.0000
17.000 1.4167 0.08587 0.08283 -0.0229 0.0135 1.0000
17.250 1.3887 0.09443 0.09151 -0.0272 0.0135 1.0000
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