ONERA OA206 AIRFOIL (oa206-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: ONERA OA206 AIRFOIL (oa206-il) Reynolds number: 100,000 Max Cl/Cd: 35.89 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-oa206-il-100000-n5.txt Download as CSV file: xf-oa206-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.6727 0.11181 0.10714 0.0327 1.0000 0.0428
-8.750 -0.6742 0.10759 0.10297 0.0264 1.0000 0.0441
-8.500 -0.6754 0.10292 0.09836 0.0196 1.0000 0.0446
-7.500 -0.6611 0.08328 0.07873 0.0100 1.0000 0.0479
-7.250 -0.6532 0.07898 0.07440 0.0079 1.0000 0.0492
-7.000 -0.6440 0.07431 0.06964 0.0049 1.0000 0.0502
-6.750 -0.6329 0.06956 0.06479 0.0020 1.0000 0.0512
-6.500 -0.6196 0.06481 0.05987 -0.0007 1.0000 0.0519
-6.250 -0.5963 0.05620 0.05058 -0.0044 1.0000 0.0319
-6.000 -0.5816 0.05167 0.04594 -0.0052 1.0000 0.0306
-5.750 -0.5630 0.04726 0.04126 -0.0061 1.0000 0.0294
-5.500 -0.5420 0.04298 0.03663 -0.0067 1.0000 0.0285
-5.250 -0.5192 0.03893 0.03216 -0.0071 1.0000 0.0279
-5.000 -0.4947 0.03538 0.02813 -0.0073 1.0000 0.0282
-4.750 -0.4686 0.03251 0.02477 -0.0072 1.0000 0.0303
-4.500 -0.4418 0.02972 0.02150 -0.0071 1.0000 0.0310
-4.250 -0.4146 0.02710 0.01843 -0.0069 1.0000 0.0311
-4.000 -0.3868 0.02485 0.01575 -0.0067 1.0000 0.0315
-3.750 -0.3588 0.02296 0.01350 -0.0064 1.0000 0.0321
-3.500 -0.3312 0.02104 0.01131 -0.0062 1.0000 0.0336
-3.250 -0.3046 0.01974 0.01000 -0.0063 1.0000 0.0375
-3.000 -0.2772 0.01851 0.00866 -0.0060 1.0000 0.0400
-2.750 -0.2503 0.01734 0.00742 -0.0057 1.0000 0.0422
-2.500 -0.2238 0.01641 0.00641 -0.0053 1.0000 0.0448
-2.250 -0.1981 0.01549 0.00555 -0.0052 1.0000 0.0522
-2.000 -0.1715 0.01484 0.00482 -0.0049 1.0000 0.0587
-1.750 -0.1453 0.01416 0.00412 -0.0047 1.0000 0.0704
-1.500 -0.1196 0.01336 0.00359 -0.0045 1.0000 0.1146
-1.250 -0.1189 0.01059 0.00386 0.0024 1.0000 0.8669
-1.000 -0.0390 0.01050 0.00351 -0.0061 1.0000 1.0000
-0.750 -0.0171 0.01044 0.00333 -0.0053 1.0000 1.0000
-0.500 0.0030 0.01042 0.00321 -0.0043 1.0000 1.0000
-0.250 0.0209 0.01042 0.00313 -0.0028 1.0000 1.0000
0.000 0.0373 0.01045 0.00311 -0.0011 1.0000 1.0000
0.250 0.0780 0.01053 0.00311 -0.0040 0.9850 1.0000
0.500 0.1177 0.01061 0.00314 -0.0067 0.9694 1.0000
0.750 0.1542 0.01070 0.00321 -0.0085 0.9517 1.0000
1.000 0.1857 0.01079 0.00330 -0.0091 0.9315 1.0000
1.250 0.2117 0.01087 0.00338 -0.0084 0.9077 1.0000
1.500 0.2352 0.01093 0.00344 -0.0071 0.8806 1.0000
1.750 0.2575 0.01096 0.00349 -0.0054 0.8501 1.0000
2.000 0.2794 0.01098 0.00349 -0.0035 0.8134 1.0000
2.250 0.3008 0.01103 0.00347 -0.0015 0.7695 1.0000
2.500 0.3225 0.01113 0.00345 0.0005 0.7146 1.0000
2.750 0.3447 0.01134 0.00349 0.0024 0.6447 1.0000
3.000 0.3675 0.01171 0.00355 0.0038 0.5624 1.0000
3.250 0.3919 0.01222 0.00372 0.0046 0.4828 1.0000
3.500 0.4175 0.01275 0.00399 0.0050 0.4212 1.0000
3.750 0.4437 0.01326 0.00433 0.0052 0.3752 1.0000
4.000 0.4703 0.01375 0.00477 0.0053 0.3356 1.0000
4.250 0.4969 0.01424 0.00520 0.0053 0.2977 1.0000
4.500 0.5236 0.01475 0.00563 0.0053 0.2551 1.0000
4.750 0.5499 0.01536 0.00604 0.0052 0.2011 1.0000
5.000 0.5761 0.01605 0.00661 0.0050 0.1497 1.0000
5.250 0.6021 0.01695 0.00731 0.0049 0.0976 1.0000
5.500 0.6276 0.01818 0.00832 0.0048 0.0591 1.0000
5.750 0.6532 0.01943 0.00960 0.0049 0.0460 1.0000
6.000 0.6783 0.02069 0.01095 0.0051 0.0378 1.0000
6.250 0.7031 0.02198 0.01241 0.0052 0.0331 1.0000
6.500 0.7263 0.02392 0.01443 0.0056 0.0305 1.0000
6.750 0.7510 0.02559 0.01638 0.0061 0.0285 1.0000
7.000 0.7754 0.02719 0.01826 0.0063 0.0254 1.0000
7.250 0.7986 0.02908 0.02037 0.0065 0.0234 1.0000
7.500 0.8204 0.03160 0.02317 0.0068 0.0224 1.0000
7.750 0.8395 0.03507 0.02707 0.0071 0.0217 1.0000
8.000 0.8564 0.03892 0.03142 0.0073 0.0213 1.0000
8.250 0.8706 0.04286 0.03596 0.0075 0.0211 1.0000
8.500 0.8801 0.04732 0.04100 0.0074 0.0209 1.0000
8.750 0.8840 0.05223 0.04645 0.0069 0.0206 1.0000
9.000 0.8812 0.05766 0.05234 0.0056 0.0203 1.0000
9.250 0.8720 0.06345 0.05846 0.0033 0.0203 1.0000
9.500 0.8569 0.06933 0.06452 -0.0003 0.0205 1.0000
9.750 0.8421 0.07671 0.07200 -0.0071 0.0208 1.0000
10.000 0.8306 0.08564 0.08095 -0.0150 0.0212 1.0000
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Polar data table (+)
Polar graphs
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