ONERA OA206 AIRFOIL (oa206-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: ONERA OA206 AIRFOIL (oa206-il) Reynolds number: 500,000 Max Cl/Cd: 56.34 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-oa206-il-500000-n5.txt Download as CSV file: xf-oa206-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5729 0.09358 0.09160 0.0248 1.0000 0.0093
-8.750 -0.5763 0.08882 0.08685 0.0232 1.0000 0.0090
-8.500 -0.7024 0.09653 0.09448 0.0348 1.0000 0.0096
-8.250 -0.7025 0.09199 0.08996 0.0317 1.0000 0.0093
-8.000 -0.7040 0.08680 0.08480 0.0268 1.0000 0.0090
-7.750 -0.7015 0.08060 0.07858 0.0198 1.0000 0.0087
-7.500 -0.6958 0.07418 0.07209 0.0140 1.0000 0.0084
-7.250 -0.6879 0.06742 0.06523 0.0089 1.0000 0.0081
-7.000 -0.6774 0.06037 0.05802 0.0048 1.0000 0.0078
-6.750 -0.6639 0.05360 0.05104 0.0019 1.0000 0.0077
-6.500 -0.6473 0.04760 0.04479 0.0001 1.0000 0.0078
-6.250 -0.6283 0.04210 0.03901 -0.0010 1.0000 0.0081
-6.000 -0.6075 0.03659 0.03316 -0.0016 1.0000 0.0084
-5.750 -0.5852 0.03093 0.02708 -0.0018 1.0000 0.0087
-5.500 -0.5613 0.02469 0.02024 -0.0014 1.0000 0.0095
-5.250 -0.5358 0.01964 0.01453 -0.0011 1.0000 0.0099
-5.000 -0.5085 0.01719 0.01167 -0.0011 1.0000 0.0102
-4.750 -0.4813 0.01487 0.00899 -0.0011 1.0000 0.0107
-4.500 -0.4531 0.01391 0.00790 -0.0014 1.0000 0.0113
-4.250 -0.4246 0.01323 0.00714 -0.0017 1.0000 0.0119
-4.000 -0.3960 0.01251 0.00635 -0.0020 1.0000 0.0125
-3.750 -0.3658 0.01186 0.00562 -0.0025 0.9835 0.0133
-3.500 -0.3364 0.01143 0.00512 -0.0029 0.9742 0.0144
-3.250 -0.3098 0.01102 0.00463 -0.0026 0.9637 0.0151
-3.000 -0.2853 0.01033 0.00386 -0.0017 0.9529 0.0160
-2.750 -0.2611 0.00993 0.00342 -0.0009 0.9426 0.0174
-2.500 -0.2365 0.00968 0.00313 0.0000 0.9333 0.0187
-2.250 -0.2101 0.00941 0.00282 0.0004 0.9239 0.0204
-2.000 -0.1840 0.00925 0.00263 0.0009 0.9143 0.0224
-1.750 -0.1579 0.00893 0.00227 0.0014 0.9041 0.0261
-1.500 -0.1316 0.00874 0.00206 0.0019 0.8917 0.0302
-1.250 -0.1046 0.00857 0.00186 0.0022 0.8785 0.0368
-1.000 -0.0772 0.00837 0.00170 0.0024 0.8661 0.0538
-0.750 -0.0499 0.00808 0.00156 0.0025 0.8520 0.1047
-0.500 -0.0226 0.00667 0.00135 0.0016 0.8358 0.4759
-0.250 -0.0026 0.00542 0.00144 0.0035 0.8163 0.8494
0.000 0.0180 0.00544 0.00146 0.0058 0.7919 0.9036
0.250 0.0378 0.00548 0.00144 0.0082 0.7625 0.9338
0.500 0.0558 0.00548 0.00134 0.0110 0.7275 0.9583
0.750 0.0811 0.00556 0.00123 0.0118 0.6833 0.9689
1.000 0.1096 0.00573 0.00117 0.0117 0.6277 0.9744
1.250 0.1398 0.00597 0.00114 0.0111 0.5604 0.9792
1.500 0.1704 0.00630 0.00115 0.0103 0.4823 0.9842
1.750 0.2021 0.00661 0.00120 0.0092 0.4168 0.9887
2.000 0.2337 0.00683 0.00127 0.0082 0.3766 0.9945
2.250 0.2641 0.00703 0.00134 0.0074 0.3457 1.0000
2.500 0.2930 0.00720 0.00142 0.0071 0.3230 1.0000
2.750 0.3219 0.00740 0.00153 0.0066 0.2982 1.0000
3.000 0.3509 0.00758 0.00165 0.0062 0.2749 1.0000
3.250 0.3799 0.00779 0.00178 0.0058 0.2483 1.0000
3.500 0.4088 0.00808 0.00193 0.0053 0.2108 1.0000
3.750 0.4376 0.00846 0.00211 0.0048 0.1655 1.0000
4.000 0.4664 0.00880 0.00234 0.0043 0.1348 1.0000
4.250 0.4951 0.00915 0.00257 0.0039 0.1060 1.0000
4.500 0.5236 0.00954 0.00283 0.0034 0.0763 1.0000
4.750 0.5519 0.01006 0.00318 0.0030 0.0422 1.0000
5.000 0.5803 0.01048 0.00357 0.0026 0.0277 1.0000
5.250 0.6087 0.01091 0.00400 0.0023 0.0204 1.0000
5.500 0.6369 0.01132 0.00442 0.0020 0.0164 1.0000
5.750 0.6650 0.01184 0.00500 0.0018 0.0139 1.0000
6.000 0.6930 0.01230 0.00553 0.0015 0.0126 1.0000
6.250 0.7208 0.01281 0.00613 0.0013 0.0114 1.0000
6.500 0.7481 0.01342 0.00679 0.0011 0.0102 1.0000
6.750 0.7750 0.01423 0.00769 0.0009 0.0092 1.0000
7.000 0.8020 0.01486 0.00842 0.0008 0.0086 1.0000
7.250 0.8286 0.01563 0.00932 0.0007 0.0080 1.0000
7.500 0.8548 0.01645 0.01025 0.0006 0.0075 1.0000
7.750 0.8806 0.01729 0.01120 0.0005 0.0071 1.0000
8.000 0.9060 0.01820 0.01222 0.0005 0.0067 1.0000
8.250 0.9302 0.01947 0.01364 0.0005 0.0063 1.0000
8.500 0.9515 0.02170 0.01614 0.0008 0.0060 1.0000
8.750 0.9743 0.02327 0.01799 0.0010 0.0059 1.0000
9.000 0.9953 0.02525 0.02027 0.0012 0.0057 1.0000
9.250 1.0138 0.02772 0.02309 0.0015 0.0056 1.0000
9.500 1.0299 0.03054 0.02629 0.0019 0.0055 1.0000
9.750 1.0429 0.03368 0.02983 0.0022 0.0053 1.0000
10.000 1.0511 0.03737 0.03392 0.0024 0.0051 1.0000
10.250 1.0527 0.04172 0.03868 0.0024 0.0049 1.0000
10.500 1.0435 0.04714 0.04448 0.0016 0.0049 1.0000
10.750 1.0219 0.05313 0.05074 -0.0009 0.0049 1.0000
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Polar data table (+)
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