ONERA OA206 AIRFOIL (oa206-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: ONERA OA206 AIRFOIL (oa206-il) Reynolds number: 200,000 Max Cl/Cd: 44.09 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-oa206-il-200000-n5.txt Download as CSV file: xf-oa206-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-6.750 -0.6406 0.05713 0.05327 -0.0005 1.0000 0.0156
-6.500 -0.6255 0.05201 0.04791 -0.0019 1.0000 0.0156
-6.250 -0.6115 0.05002 0.04590 -0.0027 1.0000 0.0168
-6.000 -0.5919 0.04738 0.04311 -0.0036 1.0000 0.0185
-5.750 -0.5709 0.04297 0.03840 -0.0044 1.0000 0.0190
-5.500 -0.5488 0.03768 0.03269 -0.0049 1.0000 0.0178
-5.250 -0.5247 0.03243 0.02690 -0.0049 1.0000 0.0170
-5.000 -0.4993 0.02822 0.02217 -0.0048 1.0000 0.0168
-4.750 -0.4729 0.02523 0.01874 -0.0047 1.0000 0.0171
-4.500 -0.4457 0.02285 0.01599 -0.0047 1.0000 0.0176
-4.250 -0.4180 0.02092 0.01374 -0.0047 1.0000 0.0185
-4.000 -0.3898 0.01963 0.01219 -0.0047 1.0000 0.0206
-3.750 -0.3615 0.01808 0.01035 -0.0046 1.0000 0.0215
-3.500 -0.3333 0.01672 0.00876 -0.0045 1.0000 0.0221
-3.250 -0.3054 0.01542 0.00733 -0.0044 1.0000 0.0229
-3.000 -0.2783 0.01411 0.00599 -0.0044 1.0000 0.0245
-2.750 -0.2506 0.01351 0.00541 -0.0046 1.0000 0.0274
-2.500 -0.2229 0.01291 0.00478 -0.0047 1.0000 0.0304
-2.250 -0.1953 0.01230 0.00410 -0.0047 1.0000 0.0324
-2.000 -0.1679 0.01161 0.00342 -0.0049 1.0000 0.0364
-1.750 -0.1406 0.01128 0.00308 -0.0050 1.0000 0.0437
-1.500 -0.1099 0.01087 0.00269 -0.0058 0.9917 0.0557
-1.250 -0.0745 0.01020 0.00236 -0.0077 0.9783 0.1400
-1.000 -0.0614 0.00772 0.00256 -0.0045 0.9648 0.8346
-0.750 -0.0450 0.00783 0.00274 -0.0005 0.9479 0.9221
-0.500 -0.0175 0.00782 0.00269 0.0009 0.9343 0.9720
-0.250 0.0416 0.00778 0.00256 -0.0053 0.9261 1.0000
0.000 0.0639 0.00777 0.00248 -0.0040 0.9102 1.0000
0.250 0.0859 0.00776 0.00240 -0.0027 0.8936 1.0000
0.500 0.1081 0.00774 0.00232 -0.0014 0.8752 1.0000
0.750 0.1305 0.00772 0.00224 0.0000 0.8537 1.0000
1.000 0.1528 0.00771 0.00216 0.0014 0.8282 1.0000
1.250 0.1752 0.00772 0.00207 0.0028 0.7969 1.0000
1.500 0.1984 0.00778 0.00199 0.0042 0.7581 1.0000
1.750 0.2223 0.00790 0.00195 0.0053 0.7103 1.0000
2.000 0.2473 0.00811 0.00192 0.0061 0.6496 1.0000
2.250 0.2731 0.00844 0.00193 0.0066 0.5744 1.0000
2.500 0.2998 0.00886 0.00200 0.0067 0.4928 1.0000
2.750 0.3271 0.00929 0.00214 0.0065 0.4275 1.0000
3.000 0.3549 0.00966 0.00235 0.0063 0.3825 1.0000
3.250 0.3828 0.00999 0.00256 0.0061 0.3480 1.0000
3.500 0.4108 0.01030 0.00279 0.0058 0.3167 1.0000
3.750 0.4388 0.01062 0.00303 0.0056 0.2859 1.0000
4.000 0.4667 0.01097 0.00332 0.0053 0.2490 1.0000
4.250 0.4944 0.01144 0.00359 0.0050 0.2001 1.0000
4.500 0.5219 0.01194 0.00392 0.0046 0.1571 1.0000
4.750 0.5494 0.01246 0.00430 0.0043 0.1197 1.0000
5.000 0.5766 0.01310 0.00479 0.0040 0.0764 1.0000
5.250 0.6036 0.01395 0.00545 0.0037 0.0423 1.0000
5.500 0.6307 0.01477 0.00626 0.0036 0.0301 1.0000
5.750 0.6579 0.01550 0.00713 0.0035 0.0256 1.0000
6.000 0.6842 0.01656 0.00828 0.0034 0.0219 1.0000
6.250 0.7106 0.01739 0.00927 0.0034 0.0193 1.0000
6.500 0.7366 0.01840 0.01041 0.0034 0.0175 1.0000
6.750 0.7619 0.01955 0.01168 0.0035 0.0162 1.0000
7.000 0.7864 0.02100 0.01324 0.0036 0.0152 1.0000
7.250 0.8088 0.02348 0.01591 0.0039 0.0144 1.0000
7.500 0.8337 0.02475 0.01750 0.0041 0.0136 1.0000
7.750 0.8577 0.02622 0.01926 0.0043 0.0123 1.0000
8.000 0.8799 0.02833 0.02172 0.0045 0.0117 1.0000
8.250 0.9002 0.03086 0.02463 0.0048 0.0112 1.0000
8.500 0.9181 0.03374 0.02793 0.0050 0.0108 1.0000
8.750 0.9329 0.03705 0.03168 0.0052 0.0105 1.0000
9.000 0.9434 0.04091 0.03599 0.0053 0.0104 1.0000
9.250 0.9479 0.04545 0.04099 0.0051 0.0103 1.0000
9.500 0.9441 0.05085 0.04684 0.0043 0.0102 1.0000
9.750 0.9294 0.05722 0.05359 0.0021 0.0103 1.0000
10.000 0.9015 0.06615 0.06281 -0.0053 0.0105 1.0000
10.250 0.8497 0.09147 0.08823 -0.0256 0.0114 1.0000
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Polar data table (+)
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