NACA 63-206 (naca63206-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 63-206 (naca63206-il) Reynolds number: 1,000,000 Max Cl/Cd: 80.34 at α=2° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca63206-il-1000000.txt Download as CSV file: xf-naca63206-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63-206
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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.5608 0.07767 0.07613 -0.0117 1.0000 0.0049
-7.750 -0.5664 0.07206 0.07056 -0.0175 1.0000 0.0051
-7.500 -0.5611 0.06632 0.06477 -0.0238 1.0000 0.0050
-7.250 -0.5561 0.06056 0.05894 -0.0283 1.0000 0.0051
-7.000 -0.5478 0.05537 0.05366 -0.0315 1.0000 0.0052
-6.750 -0.5364 0.05095 0.04913 -0.0337 1.0000 0.0054
-6.500 -0.5226 0.04752 0.04560 -0.0351 1.0000 0.0057
-6.250 -0.5065 0.04403 0.04198 -0.0362 1.0000 0.0061
-6.000 -0.4884 0.04034 0.03813 -0.0370 1.0000 0.0070
-4.000 -0.3055 0.01329 0.00878 -0.0340 0.9987 0.0082
-3.750 -0.2719 0.01082 0.00601 -0.0350 0.9967 0.0081
-3.250 -0.2050 0.00831 0.00322 -0.0376 0.9910 0.0112
-3.000 -0.1708 0.00783 0.00271 -0.0391 0.9872 0.0129
-2.750 -0.1357 0.00746 0.00230 -0.0407 0.9837 0.0158
-2.500 -0.1023 0.00725 0.00208 -0.0420 0.9780 0.0172
-2.250 -0.0690 0.00670 0.00139 -0.0432 0.9708 0.0208
-2.000 -0.0375 0.00637 0.00107 -0.0439 0.9612 0.0411
-1.750 -0.0087 0.00537 0.00083 -0.0448 0.9494 0.2793
-1.500 0.0179 0.00455 0.00071 -0.0450 0.9358 0.5087
-1.250 0.0441 0.00422 0.00067 -0.0448 0.9217 0.6174
-1.000 0.0699 0.00400 0.00067 -0.0443 0.9076 0.7027
-0.750 0.0959 0.00389 0.00067 -0.0437 0.8936 0.7564
-0.500 0.1215 0.00381 0.00069 -0.0431 0.8794 0.8038
-0.250 0.1475 0.00378 0.00069 -0.0425 0.8650 0.8322
0.000 0.1735 0.00378 0.00070 -0.0420 0.8493 0.8532
0.250 0.1993 0.00379 0.00070 -0.0414 0.8322 0.8737
0.500 0.2251 0.00381 0.00072 -0.0408 0.8144 0.8914
0.750 0.2503 0.00384 0.00074 -0.0400 0.7953 0.9090
1.000 0.2749 0.00389 0.00075 -0.0391 0.7700 0.9277
1.250 0.2980 0.00398 0.00074 -0.0379 0.7291 0.9483
1.500 0.3247 0.00410 0.00073 -0.0375 0.6844 0.9734
1.750 0.3550 0.00442 0.00077 -0.0382 0.6007 1.0000
2.000 0.3816 0.00475 0.00086 -0.0381 0.5315 1.0000
2.250 0.4066 0.00541 0.00102 -0.0379 0.3981 1.0000
2.500 0.4288 0.00677 0.00140 -0.0377 0.1453 1.0000
2.750 0.4542 0.00758 0.00175 -0.0376 0.0298 1.0000
3.000 0.4814 0.00798 0.00217 -0.0374 0.0198 1.0000
3.250 0.5088 0.00825 0.00249 -0.0374 0.0175 1.0000
3.500 0.5359 0.00863 0.00292 -0.0373 0.0149 1.0000
3.750 0.5624 0.00917 0.00352 -0.0370 0.0130 1.0000
4.000 0.5862 0.01049 0.00501 -0.0363 0.0115 1.0000
4.250 0.6125 0.01105 0.00562 -0.0360 0.0105 1.0000
4.500 0.6389 0.01162 0.00624 -0.0357 0.0094 1.0000
4.750 0.6648 0.01237 0.00709 -0.0354 0.0084 1.0000
5.000 0.6906 0.01323 0.00802 -0.0350 0.0077 1.0000
5.250 0.7165 0.01391 0.00877 -0.0348 0.0070 1.0000
5.750 0.7640 0.01841 0.01379 -0.0332 0.0051 1.0000
6.000 0.7846 0.02306 0.01898 -0.0315 0.0051 1.0000
6.250 0.8023 0.03126 0.02790 -0.0282 0.0072 1.0000
6.500 0.8206 0.03473 0.03164 -0.0272 0.0070 1.0000
6.750 0.8372 0.03813 0.03528 -0.0265 0.0067 1.0000
7.000 0.8520 0.04152 0.03888 -0.0259 0.0065 1.0000
7.250 0.8635 0.04557 0.04316 -0.0252 0.0063 1.0000
7.500 0.8710 0.05014 0.04799 -0.0248 0.0062 1.0000
7.750 0.8708 0.05597 0.05405 -0.0245 0.0060 1.0000
8.000 0.8625 0.06290 0.06116 -0.0247 0.0058 1.0000
8.250 0.8171 0.05909 0.05765 -0.0235 0.0060 1.0000
8.500 0.7984 0.06322 0.06184 -0.0230 0.0061 1.0000
8.750 0.7758 0.06954 0.06823 -0.0266 0.0062 1.0000
9.000 0.7515 0.08087 0.07960 -0.0358 0.0065 1.0000
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Polar data table (+)
Polar graphs
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