NACA 63-206 (naca63206-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 63-206 (naca63206-il) Reynolds number: 50,000 Max Cl/Cd: 24.23 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca63206-il-50000.txt Download as CSV file: xf-naca63206-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.5540 0.09594 0.08931 0.0090 1.0000 0.2794
-7.500 -0.5629 0.09395 0.08745 0.0084 1.0000 0.2955
-7.250 -0.5497 0.09001 0.08353 0.0104 1.0000 0.3215
-7.000 -0.5441 0.08687 0.08045 0.0121 1.0000 0.3487
-6.750 -0.5275 0.08292 0.07652 0.0146 1.0000 0.3803
-6.500 -0.5234 0.08037 0.07404 0.0171 1.0000 0.4159
-6.250 -0.5106 0.07718 0.07088 0.0202 1.0000 0.4565
-6.000 -0.4862 0.07299 0.06667 0.0230 1.0000 0.5014
-5.750 -0.4749 0.07037 0.06407 0.0266 1.0000 0.5512
-5.000 -0.4560 0.04602 0.03857 -0.0338 1.0000 0.2001
-4.750 -0.4183 0.03989 0.03149 -0.0375 1.0000 0.1415
-4.500 -0.3863 0.03598 0.02666 -0.0383 1.0000 0.1191
-4.250 -0.3591 0.03256 0.02278 -0.0382 1.0000 0.1130
-4.000 -0.3321 0.02995 0.01970 -0.0378 1.0000 0.1156
-3.750 -0.3041 0.02742 0.01672 -0.0371 1.0000 0.1144
-3.500 -0.2764 0.02518 0.01400 -0.0360 1.0000 0.1137
-3.250 -0.2498 0.02329 0.01188 -0.0345 1.0000 0.1168
-3.000 -0.2249 0.02161 0.01008 -0.0328 1.0000 0.1237
-2.750 -0.2014 0.02016 0.00865 -0.0314 1.0000 0.1486
-2.500 -0.1776 0.01842 0.00712 -0.0304 1.0000 0.1849
-2.250 -0.1312 0.01450 0.00602 -0.0261 1.0000 1.0000
-2.000 -0.1189 0.01430 0.00544 -0.0241 1.0000 1.0000
-1.750 -0.1027 0.01416 0.00488 -0.0228 1.0000 1.0000
-1.500 -0.0834 0.01408 0.00448 -0.0219 1.0000 1.0000
-1.250 -0.0626 0.01404 0.00417 -0.0212 1.0000 1.0000
-1.000 -0.0410 0.01404 0.00393 -0.0206 1.0000 1.0000
-0.750 -0.0189 0.01406 0.00376 -0.0202 1.0000 1.0000
-0.500 0.0032 0.01412 0.00365 -0.0197 1.0000 1.0000
-0.250 0.0255 0.01421 0.00356 -0.0192 1.0000 1.0000
0.000 0.0478 0.01433 0.00357 -0.0188 1.0000 1.0000
0.250 0.0699 0.01449 0.00363 -0.0184 1.0000 1.0000
0.500 0.0919 0.01467 0.00376 -0.0181 1.0000 1.0000
0.750 0.1136 0.01488 0.00394 -0.0177 1.0000 1.0000
1.000 0.1352 0.01513 0.00419 -0.0174 1.0000 1.0000
1.250 0.1564 0.01542 0.00451 -0.0171 1.0000 1.0000
1.500 0.1773 0.01575 0.00487 -0.0168 1.0000 1.0000
1.750 0.1979 0.01612 0.00530 -0.0165 1.0000 1.0000
2.000 0.2182 0.01655 0.00580 -0.0163 1.0000 1.0000
2.250 0.2382 0.01702 0.00638 -0.0162 1.0000 1.0000
2.500 0.2577 0.01755 0.00704 -0.0161 1.0000 1.0000
2.750 0.2768 0.01814 0.00787 -0.0160 1.0000 1.0000
3.000 0.2954 0.01880 0.00870 -0.0161 1.0000 1.0000
3.250 0.3136 0.01953 0.00963 -0.0162 1.0000 1.0000
3.500 0.3313 0.02034 0.01067 -0.0164 1.0000 1.0000
3.750 0.3484 0.02125 0.01183 -0.0166 1.0000 1.0000
4.000 0.5438 0.02244 0.01083 -0.0240 0.1400 1.0000
4.250 0.5708 0.02460 0.01287 -0.0228 0.1230 1.0000
4.500 0.6028 0.02674 0.01520 -0.0218 0.1147 1.0000
4.750 0.6328 0.02934 0.01792 -0.0211 0.1066 1.0000
5.000 0.6606 0.03184 0.02068 -0.0204 0.0986 1.0000
5.250 0.6893 0.03488 0.02433 -0.0194 0.1002 1.0000
5.500 0.7159 0.03849 0.02868 -0.0184 0.1049 1.0000
5.750 0.7413 0.04235 0.03308 -0.0174 0.1115 1.0000
6.000 0.7648 0.04686 0.03850 -0.0166 0.1265 1.0000
6.250 0.7864 0.05259 0.04515 -0.0170 0.1545 1.0000
6.500 0.8045 0.06285 0.05667 -0.0252 0.2455 1.0000
6.750 0.7233 0.06121 0.05569 -0.0304 0.2745 1.0000
7.000 0.6519 0.07422 0.06859 -0.0487 0.3911 1.0000
8.000 0.7327 0.09996 0.09370 -0.0639 0.3979 1.0000
8.250 0.7589 0.10548 0.09927 -0.0625 0.3766 1.0000
8.750 0.7599 0.11232 0.10611 -0.0614 0.3348 1.0000
9.000 0.7586 0.11550 0.10924 -0.0614 0.3147 1.0000
9.250 0.7718 0.12019 0.11394 -0.0603 0.2947 1.0000
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Polar data table (+)
Polar graphs
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