ONERA OA206 AIRFOIL (oa206-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: ONERA OA206 AIRFOIL (oa206-il) Reynolds number: 200,000 Max Cl/Cd: 46.08 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-oa206-il-200000.txt Download as CSV file: xf-oa206-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: ONERA OA206 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.6872 0.12000 0.11670 0.0390 1.0000 0.0318
-9.250 -0.6855 0.11600 0.11273 0.0346 1.0000 0.0322
-9.000 -0.6834 0.11178 0.10853 0.0303 1.0000 0.0324
-8.750 -0.6816 0.10728 0.10406 0.0258 1.0000 0.0325
-8.500 -0.6798 0.10242 0.09922 0.0204 1.0000 0.0326
-8.250 -0.6773 0.09744 0.09420 0.0149 1.0000 0.0326
-8.000 -0.6723 0.09252 0.08921 0.0107 1.0000 0.0327
-7.750 -0.6661 0.08770 0.08429 0.0073 1.0000 0.0327
-7.500 -0.6703 0.07941 0.07610 0.0071 1.0000 0.0339
-7.250 -0.6626 0.07552 0.07223 0.0070 1.0000 0.0347
-7.000 -0.6528 0.07156 0.06822 0.0057 1.0000 0.0357
-6.750 -0.6410 0.06734 0.06392 0.0036 1.0000 0.0371
-6.500 -0.6269 0.06292 0.05938 0.0012 1.0000 0.0389
-6.250 -0.6095 0.05838 0.05465 -0.0012 1.0000 0.0415
-6.000 -0.5801 0.05677 0.05231 -0.0035 1.0000 0.0450
-5.750 -0.5709 0.04848 0.04408 -0.0051 1.0000 0.0470
-5.500 -0.5526 0.04548 0.04107 -0.0056 1.0000 0.0498
-5.250 -0.5300 0.04231 0.03768 -0.0062 1.0000 0.0536
-5.000 -0.5035 0.03891 0.03359 -0.0068 1.0000 0.0599
-4.750 -0.4819 0.03540 0.03015 -0.0074 1.0000 0.0626
-4.500 -0.4506 0.03674 0.03080 -0.0068 1.0000 0.0724
-4.250 -0.4306 0.03013 0.02435 -0.0082 1.0000 0.0767
-4.000 -0.4040 0.02800 0.02192 -0.0085 1.0000 0.0894
-3.750 -0.3778 0.02591 0.01965 -0.0089 1.0000 0.1039
-3.500 -0.3388 0.02209 0.01493 -0.0069 1.0000 0.0568
-3.250 -0.3073 0.01954 0.01185 -0.0061 1.0000 0.0456
-3.000 -0.2785 0.01759 0.00973 -0.0059 1.0000 0.0445
-2.750 -0.2498 0.01618 0.00816 -0.0057 1.0000 0.0449
-2.250 -0.1953 0.01334 0.00534 -0.0055 1.0000 0.0527
-2.000 -0.1680 0.01251 0.00450 -0.0054 1.0000 0.0565
-1.750 -0.1413 0.01159 0.00364 -0.0053 1.0000 0.0632
-1.500 -0.1146 0.01098 0.00307 -0.0053 1.0000 0.0792
-1.250 -0.0995 0.00770 0.00257 -0.0036 1.0000 0.7453
-1.000 -0.0553 0.00772 0.00290 -0.0026 1.0000 0.9941
-0.750 -0.0155 0.00767 0.00271 -0.0054 1.0000 1.0000
-0.500 0.0055 0.00764 0.00262 -0.0046 1.0000 1.0000
-0.250 0.0207 0.00765 0.00257 -0.0027 1.0000 1.0000
0.000 0.0321 0.00770 0.00258 -0.0001 1.0000 1.0000
0.250 0.0561 0.00777 0.00261 0.0000 0.9976 1.0000
0.500 0.1062 0.00780 0.00261 -0.0047 0.9885 1.0000
0.750 0.1545 0.00783 0.00264 -0.0090 0.9761 1.0000
1.000 0.1938 0.00790 0.00271 -0.0111 0.9582 1.0000
1.250 0.2176 0.00800 0.00281 -0.0098 0.9352 1.0000
1.500 0.2357 0.00805 0.00286 -0.0071 0.9114 1.0000
1.750 0.2540 0.00805 0.00286 -0.0045 0.8873 1.0000
2.000 0.2737 0.00802 0.00282 -0.0021 0.8604 1.0000
2.250 0.2947 0.00798 0.00275 -0.0001 0.8280 1.0000
2.500 0.3162 0.00798 0.00268 0.0019 0.7879 1.0000
2.750 0.3386 0.00808 0.00265 0.0037 0.7329 1.0000
3.000 0.3622 0.00834 0.00263 0.0052 0.6539 1.0000
3.250 0.3871 0.00884 0.00270 0.0059 0.5516 1.0000
3.500 0.4137 0.00945 0.00290 0.0060 0.4602 1.0000
3.750 0.4409 0.01002 0.00319 0.0059 0.3999 1.0000
4.000 0.4684 0.01053 0.00355 0.0056 0.3501 1.0000
4.250 0.4959 0.01102 0.00385 0.0054 0.2982 1.0000
4.500 0.5236 0.01146 0.00414 0.0051 0.2473 1.0000
4.750 0.5511 0.01196 0.00448 0.0048 0.1994 1.0000
5.000 0.5784 0.01260 0.00495 0.0044 0.1422 1.0000
5.250 0.6047 0.01414 0.00600 0.0041 0.0611 1.0000
5.500 0.6315 0.01533 0.00718 0.0041 0.0464 1.0000
5.750 0.6571 0.01695 0.00883 0.0043 0.0404 1.0000
6.000 0.6837 0.01792 0.00989 0.0044 0.0350 1.0000
6.250 0.7088 0.01969 0.01172 0.0047 0.0322 1.0000
6.500 0.7330 0.02292 0.01517 0.0052 0.0307 1.0000
6.750 0.7588 0.02511 0.01770 0.0056 0.0303 1.0000
7.000 0.7838 0.02745 0.02045 0.0059 0.0296 1.0000
7.250 0.8079 0.02957 0.02302 0.0063 0.0278 1.0000
7.500 0.8279 0.03361 0.02763 0.0067 0.0282 1.0000
7.750 0.8427 0.03893 0.03349 0.0068 0.0294 1.0000
11.750 0.6292 0.13132 0.12806 -0.0258 0.0524 1.0000
12.000 0.6191 0.13544 0.13216 -0.0290 0.0502 1.0000
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Polar data table (+)
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