NACA 63-206 (naca63206-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 63-206 (naca63206-il) Reynolds number: 500,000 Max Cl/Cd: 72.44 at α=2.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca63206-il-500000.txt Download as CSV file: xf-naca63206-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5410 0.08706 0.08483 -0.0090 1.0000 0.0093
-8.000 -0.5401 0.08293 0.08073 -0.0115 1.0000 0.0093
-7.750 -0.5451 0.07767 0.07554 -0.0155 1.0000 0.0093
-7.500 -0.5411 0.07199 0.06984 -0.0219 1.0000 0.0094
-7.250 -0.5442 0.06448 0.06226 -0.0272 1.0000 0.0096
-7.000 -0.5395 0.05887 0.05656 -0.0305 1.0000 0.0099
-6.750 -0.5314 0.05419 0.05177 -0.0327 1.0000 0.0102
-6.500 -0.5203 0.05083 0.04833 -0.0340 1.0000 0.0108
-6.250 -0.5060 0.04734 0.04472 -0.0352 1.0000 0.0117
-6.000 -0.4890 0.04360 0.04082 -0.0363 1.0000 0.0130
-5.750 -0.4690 0.03987 0.03683 -0.0369 1.0000 0.0147
-5.500 -0.4379 0.03956 0.03626 -0.0358 1.0000 0.0172
-3.750 -0.2880 0.01533 0.00988 -0.0328 1.0000 0.0149
-3.500 -0.2634 0.01332 0.00761 -0.0317 1.0000 0.0151
-3.250 -0.2399 0.01230 0.00642 -0.0307 1.0000 0.0164
-3.000 -0.2170 0.01117 0.00519 -0.0298 1.0000 0.0185
-2.750 -0.1878 0.00989 0.00384 -0.0302 0.9988 0.0203
-2.500 -0.1507 0.00914 0.00303 -0.0323 0.9955 0.0239
-2.250 -0.1140 0.00869 0.00253 -0.0343 0.9917 0.0278
-2.000 -0.0773 0.00810 0.00186 -0.0363 0.9873 0.0388
-1.750 -0.0430 0.00605 0.00140 -0.0392 0.9842 0.4998
-1.500 -0.0084 0.00541 0.00142 -0.0409 0.9799 0.6910
-1.250 0.0245 0.00517 0.00144 -0.0418 0.9730 0.7738
-1.000 0.0558 0.00500 0.00147 -0.0421 0.9659 0.8405
-0.750 0.0844 0.00490 0.00146 -0.0418 0.9562 0.8809
-0.500 0.1118 0.00484 0.00142 -0.0413 0.9445 0.9035
-0.250 0.1368 0.00479 0.00137 -0.0403 0.9316 0.9244
0.000 0.1615 0.00474 0.00131 -0.0392 0.9183 0.9450
0.250 0.1903 0.00469 0.00125 -0.0392 0.9054 0.9661
0.500 0.2262 0.00466 0.00121 -0.0408 0.8928 0.9865
0.750 0.2569 0.00468 0.00118 -0.0414 0.8770 1.0000
1.000 0.2831 0.00475 0.00118 -0.0411 0.8594 1.0000
1.250 0.3096 0.00482 0.00120 -0.0407 0.8397 1.0000
1.500 0.3350 0.00492 0.00120 -0.0400 0.8091 1.0000
1.750 0.3599 0.00508 0.00123 -0.0392 0.7661 1.0000
2.000 0.3841 0.00534 0.00123 -0.0382 0.6959 1.0000
2.250 0.4093 0.00565 0.00130 -0.0376 0.6302 1.0000
2.500 0.4335 0.00615 0.00142 -0.0370 0.5267 1.0000
2.750 0.4521 0.00793 0.00186 -0.0362 0.2031 1.0000
3.000 0.4747 0.00942 0.00262 -0.0357 0.0311 1.0000
3.250 0.5016 0.00986 0.00316 -0.0355 0.0262 1.0000
3.500 0.5271 0.01068 0.00406 -0.0351 0.0218 1.0000
3.750 0.5504 0.01216 0.00566 -0.0342 0.0201 1.0000
4.000 0.5775 0.01249 0.00604 -0.0341 0.0185 1.0000
4.250 0.6030 0.01350 0.00713 -0.0335 0.0170 1.0000
4.500 0.6285 0.01493 0.00868 -0.0328 0.0157 1.0000
4.750 0.6544 0.01721 0.01117 -0.0318 0.0160 1.0000
5.000 0.6804 0.01851 0.01266 -0.0314 0.0144 1.0000
5.250 0.7049 0.01965 0.01389 -0.0313 0.0124 1.0000
5.500 0.7279 0.02327 0.01789 -0.0302 0.0118 1.0000
5.750 0.7316 0.01737 0.01321 -0.0257 0.0154 1.0000
6.000 0.7506 0.02070 0.01686 -0.0247 0.0144 1.0000
6.250 0.7678 0.02430 0.02075 -0.0240 0.0137 1.0000
6.500 0.7829 0.02809 0.02478 -0.0234 0.0131 1.0000
6.750 0.7954 0.03205 0.02893 -0.0229 0.0126 1.0000
7.000 0.8049 0.03666 0.03375 -0.0224 0.0122 1.0000
7.250 0.8084 0.04227 0.03959 -0.0220 0.0119 1.0000
7.500 0.8016 0.04973 0.04728 -0.0218 0.0115 1.0000
7.750 0.7863 0.05766 0.05542 -0.0218 0.0113 1.0000
8.000 0.8246 0.07159 0.06928 -0.0242 0.0111 1.0000
8.250 0.8197 0.07619 0.07400 -0.0250 0.0111 1.0000
8.500 0.8079 0.08030 0.07818 -0.0256 0.0111 1.0000
8.750 0.7964 0.08525 0.08320 -0.0287 0.0111 1.0000
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Polar data table (+)
Polar graphs
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