NACA 63-206 (naca63206-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 63-206 (naca63206-il) Reynolds number: 500,000 Max Cl/Cd: 58.7 at α=1.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca63206-il-500000-n5.txt Download as CSV file: xf-naca63206-il-500000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.5487 0.08243 0.08020 -0.0075 1.0000 0.0033
-7.750 -0.5516 0.07818 0.07599 -0.0100 1.0000 0.0032
-7.500 -0.5520 0.07360 0.07143 -0.0145 1.0000 0.0032
-7.250 -0.5481 0.06762 0.06543 -0.0212 1.0000 0.0031
-7.000 -0.5411 0.06199 0.05974 -0.0262 1.0000 0.0030
-6.750 -0.5317 0.05651 0.05415 -0.0300 1.0000 0.0030
-6.500 -0.5196 0.05123 0.04873 -0.0328 1.0000 0.0029
-6.250 -0.5052 0.04608 0.04340 -0.0349 1.0000 0.0028
-6.000 -0.4886 0.04087 0.03796 -0.0363 1.0000 0.0027
-5.750 -0.4700 0.03590 0.03271 -0.0370 1.0000 0.0026
-5.500 -0.4497 0.03095 0.02741 -0.0371 1.0000 0.0026
-5.250 -0.4279 0.02590 0.02194 -0.0368 1.0000 0.0025
-5.000 -0.4047 0.02042 0.01588 -0.0359 1.0000 0.0024
-4.750 -0.3803 0.01531 0.01007 -0.0348 1.0000 0.0024
-4.500 -0.3560 0.01242 0.00663 -0.0339 1.0000 0.0026
-4.250 -0.3316 0.01095 0.00491 -0.0332 1.0000 0.0029
-4.000 -0.2993 0.01014 0.00402 -0.0343 0.9963 0.0042
-3.750 -0.2663 0.01001 0.00388 -0.0356 0.9914 0.0072
-3.500 -0.2330 0.01008 0.00398 -0.0371 0.9863 0.0103
-3.250 -0.2004 0.01002 0.00396 -0.0384 0.9799 0.0149
-3.000 -0.1674 0.00927 0.00309 -0.0396 0.9735 0.0148
-2.750 -0.1342 0.00873 0.00243 -0.0409 0.9660 0.0152
-2.500 -0.1017 0.00831 0.00185 -0.0419 0.9567 0.0163
-2.250 -0.0697 0.00808 0.00155 -0.0428 0.9465 0.0191
-2.000 -0.0391 0.00786 0.00132 -0.0433 0.9348 0.0301
-1.750 -0.0102 0.00761 0.00115 -0.0436 0.9218 0.0644
-1.500 0.0174 0.00718 0.00100 -0.0438 0.9081 0.1609
-1.250 0.0426 0.00584 0.00087 -0.0443 0.8940 0.5274
-1.000 0.0662 0.00525 0.00097 -0.0434 0.8797 0.7265
-0.750 0.0918 0.00515 0.00095 -0.0426 0.8654 0.7710
-0.500 0.1179 0.00513 0.00093 -0.0421 0.8512 0.7953
-0.250 0.1441 0.00512 0.00092 -0.0416 0.8372 0.8149
0.000 0.1705 0.00513 0.00091 -0.0412 0.8233 0.8313
0.500 0.2227 0.00516 0.00094 -0.0401 0.7954 0.8635
0.750 0.2483 0.00518 0.00096 -0.0395 0.7787 0.8805
1.000 0.2734 0.00522 0.00099 -0.0387 0.7589 0.8987
1.250 0.2977 0.00528 0.00101 -0.0377 0.7304 0.9181
1.500 0.3211 0.00547 0.00100 -0.0366 0.6733 0.9401
1.750 0.3462 0.00596 0.00100 -0.0360 0.5473 0.9660
2.000 0.3730 0.00693 0.00123 -0.0365 0.3485 1.0000
2.250 0.3975 0.00776 0.00150 -0.0364 0.2040 1.0000
2.500 0.4225 0.00855 0.00181 -0.0364 0.0800 1.0000
2.750 0.4488 0.00906 0.00210 -0.0363 0.0294 1.0000
3.000 0.4760 0.00939 0.00245 -0.0362 0.0210 1.0000
3.250 0.5032 0.00970 0.00281 -0.0362 0.0184 1.0000
3.500 0.5301 0.01005 0.00319 -0.0361 0.0162 1.0000
3.750 0.5566 0.01049 0.00370 -0.0359 0.0150 1.0000
4.000 0.5822 0.01123 0.00462 -0.0356 0.0133 1.0000
4.250 0.6075 0.01199 0.00547 -0.0352 0.0120 1.0000
4.500 0.6336 0.01256 0.00612 -0.0350 0.0111 1.0000
4.750 0.6585 0.01361 0.00730 -0.0344 0.0104 1.0000
5.000 0.6843 0.01434 0.00813 -0.0341 0.0091 1.0000
5.250 0.7103 0.01490 0.00878 -0.0339 0.0075 1.0000
5.500 0.7366 0.01525 0.00916 -0.0338 0.0059 1.0000
5.750 0.7583 0.01827 0.01255 -0.0326 0.0048 1.0000
6.000 0.7818 0.02074 0.01538 -0.0316 0.0045 1.0000
6.250 0.8057 0.02257 0.01749 -0.0310 0.0038 1.0000
6.500 0.8296 0.02391 0.01903 -0.0305 0.0029 1.0000
6.750 0.8547 0.02396 0.01923 -0.0305 0.0023 1.0000
7.000 0.8769 0.02570 0.02123 -0.0300 0.0020 1.0000
7.250 0.8879 0.03331 0.02957 -0.0277 0.0018 1.0000
7.500 0.8866 0.04432 0.04132 -0.0252 0.0016 1.0000
7.750 0.8932 0.05033 0.04765 -0.0244 0.0015 1.0000
8.000 0.8958 0.05644 0.05402 -0.0242 0.0015 1.0000
8.250 0.8934 0.06254 0.06033 -0.0245 0.0015 1.0000
8.500 0.8860 0.06859 0.06655 -0.0257 0.0015 1.0000
8.750 0.8740 0.07407 0.07213 -0.0272 0.0015 1.0000
9.000 0.8555 0.07974 0.07786 -0.0306 0.0015 1.0000
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Polar data table (+)
Polar graphs
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