NACA 64A210 (naca64a210-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 64A210 (naca64a210-il) Reynolds number: 500,000 Max Cl/Cd: 68.52 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca64a210-il-500000-n5.txt Download as CSV file: xf-naca64a210-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64A210
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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.6156 0.09629 0.09401 -0.0154 1.0000 0.0074
-10.750 -0.6329 0.08722 0.08500 -0.0205 1.0000 0.0075
-9.750 -0.8164 0.03096 0.02716 -0.0447 1.0000 0.0075
-9.500 -0.8128 0.02765 0.02339 -0.0424 1.0000 0.0077
-9.250 -0.8065 0.02517 0.02060 -0.0400 1.0000 0.0080
-9.000 -0.7932 0.02407 0.01937 -0.0382 1.0000 0.0082
-8.750 -0.7644 0.02309 0.01827 -0.0394 0.9969 0.0085
-8.500 -0.7345 0.02228 0.01733 -0.0408 0.9941 0.0089
-8.250 -0.7059 0.02126 0.01615 -0.0418 0.9904 0.0095
-8.000 -0.6766 0.01996 0.01461 -0.0429 0.9872 0.0102
-7.750 -0.6481 0.01870 0.01311 -0.0436 0.9832 0.0107
-7.500 -0.6192 0.01774 0.01196 -0.0443 0.9787 0.0110
-7.250 -0.5914 0.01621 0.01027 -0.0451 0.9746 0.0118
-7.000 -0.5636 0.01555 0.00954 -0.0456 0.9687 0.0123
-6.750 -0.5334 0.01504 0.00898 -0.0464 0.9642 0.0131
-6.500 -0.5059 0.01453 0.00838 -0.0467 0.9577 0.0139
-6.250 -0.4779 0.01389 0.00765 -0.0470 0.9516 0.0146
-6.000 -0.4517 0.01330 0.00696 -0.0469 0.9445 0.0151
-5.750 -0.4250 0.01279 0.00637 -0.0468 0.9376 0.0155
-5.500 -0.4005 0.01206 0.00556 -0.0464 0.9299 0.0165
-5.250 -0.3747 0.01160 0.00505 -0.0461 0.9226 0.0177
-5.000 -0.3489 0.01123 0.00462 -0.0458 0.9148 0.0187
-4.500 -0.2967 0.01057 0.00383 -0.0453 0.8996 0.0210
-4.250 -0.2703 0.01031 0.00348 -0.0450 0.8924 0.0221
-4.000 -0.2442 0.00996 0.00310 -0.0447 0.8842 0.0253
-3.750 -0.2176 0.00973 0.00284 -0.0445 0.8769 0.0297
-3.500 -0.1910 0.00949 0.00259 -0.0443 0.8688 0.0372
-3.250 -0.1643 0.00927 0.00237 -0.0442 0.8612 0.0492
-3.000 -0.1377 0.00904 0.00217 -0.0440 0.8530 0.0691
-2.750 -0.1116 0.00869 0.00197 -0.0439 0.8450 0.1149
-2.500 -0.0872 0.00806 0.00173 -0.0436 0.8364 0.2305
-2.250 -0.0643 0.00719 0.00149 -0.0433 0.8273 0.4110
-2.000 -0.0393 0.00682 0.00141 -0.0429 0.8186 0.5096
-1.750 -0.0128 0.00667 0.00136 -0.0426 0.8092 0.5553
-1.500 0.0134 0.00652 0.00133 -0.0423 0.7998 0.6032
-1.250 0.0392 0.00639 0.00134 -0.0418 0.7907 0.6540
-1.000 0.0660 0.00634 0.00133 -0.0415 0.7812 0.6809
-0.750 0.0933 0.00632 0.00130 -0.0414 0.7720 0.6957
-0.500 0.1208 0.00633 0.00127 -0.0412 0.7628 0.7064
-0.250 0.1485 0.00633 0.00126 -0.0412 0.7534 0.7162
0.000 0.1760 0.00634 0.00126 -0.0411 0.7447 0.7256
0.250 0.2036 0.00635 0.00127 -0.0411 0.7355 0.7352
0.500 0.2312 0.00637 0.00128 -0.0410 0.7263 0.7450
0.750 0.2587 0.00639 0.00130 -0.0409 0.7178 0.7548
1.000 0.2862 0.00641 0.00134 -0.0409 0.7085 0.7649
1.250 0.3137 0.00643 0.00138 -0.0408 0.6995 0.7754
1.500 0.3409 0.00646 0.00142 -0.0406 0.6899 0.7858
1.750 0.3678 0.00650 0.00147 -0.0404 0.6759 0.7970
2.000 0.3942 0.00655 0.00153 -0.0401 0.6570 0.8090
2.250 0.4197 0.00664 0.00158 -0.0396 0.6281 0.8222
2.500 0.4441 0.00680 0.00164 -0.0388 0.5865 0.8380
2.750 0.4682 0.00698 0.00175 -0.0380 0.5444 0.8585
3.000 0.4920 0.00718 0.00188 -0.0372 0.4981 0.8853
3.250 0.5164 0.00755 0.00207 -0.0365 0.4275 0.9196
3.500 0.5433 0.00857 0.00248 -0.0371 0.2791 0.9546
3.750 0.5721 0.00970 0.00298 -0.0383 0.1355 0.9832
4.000 0.6021 0.01035 0.00333 -0.0394 0.0744 1.0000
4.250 0.6255 0.01074 0.00361 -0.0387 0.0510 1.0000
4.500 0.6497 0.01107 0.00389 -0.0382 0.0382 1.0000
4.750 0.6739 0.01142 0.00420 -0.0377 0.0295 1.0000
5.000 0.6985 0.01173 0.00452 -0.0372 0.0250 1.0000
5.250 0.7224 0.01215 0.00492 -0.0366 0.0209 1.0000
5.500 0.7469 0.01249 0.00531 -0.0361 0.0194 1.0000
5.750 0.7710 0.01288 0.00575 -0.0355 0.0180 1.0000
6.000 0.7947 0.01331 0.00621 -0.0350 0.0168 1.0000
6.250 0.8178 0.01384 0.00676 -0.0343 0.0157 1.0000
6.500 0.8394 0.01453 0.00750 -0.0334 0.0147 1.0000
6.750 0.8624 0.01505 0.00808 -0.0327 0.0143 1.0000
7.000 0.8848 0.01564 0.00875 -0.0319 0.0140 1.0000
7.250 0.9068 0.01627 0.00946 -0.0311 0.0136 1.0000
7.500 0.9285 0.01696 0.01022 -0.0303 0.0132 1.0000
7.750 0.9499 0.01769 0.01103 -0.0294 0.0128 1.0000
8.000 0.9716 0.01837 0.01177 -0.0286 0.0123 1.0000
8.250 0.9935 0.01898 0.01246 -0.0279 0.0117 1.0000
8.500 1.0149 0.01965 0.01317 -0.0272 0.0113 1.0000
8.750 1.0347 0.02056 0.01415 -0.0262 0.0109 1.0000
9.000 1.0514 0.02209 0.01581 -0.0249 0.0104 1.0000
9.250 1.0702 0.02328 0.01715 -0.0238 0.0101 1.0000
9.500 1.0897 0.02427 0.01828 -0.0228 0.0099 1.0000
9.750 1.1085 0.02528 0.01945 -0.0218 0.0095 1.0000
10.000 1.1264 0.02634 0.02068 -0.0207 0.0091 1.0000
10.250 1.1433 0.02744 0.02193 -0.0195 0.0087 1.0000
10.500 1.1587 0.02863 0.02327 -0.0182 0.0084 1.0000
10.750 1.1727 0.02984 0.02463 -0.0167 0.0081 1.0000
11.000 1.1845 0.03099 0.02590 -0.0150 0.0079 1.0000
11.250 1.1941 0.03218 0.02721 -0.0131 0.0077 1.0000
11.500 1.2015 0.03352 0.02868 -0.0110 0.0075 1.0000
11.750 1.2055 0.03518 0.03049 -0.0089 0.0073 1.0000
12.000 1.2021 0.03771 0.03323 -0.0065 0.0072 1.0000
12.250 1.1935 0.04089 0.03668 -0.0042 0.0070 1.0000
12.500 1.1885 0.04371 0.03975 -0.0027 0.0069 1.0000
12.750 1.1801 0.04707 0.04335 -0.0016 0.0068 1.0000
13.000 1.1679 0.05109 0.04763 -0.0012 0.0068 1.0000
13.250 1.1518 0.05594 0.05272 -0.0017 0.0067 1.0000
13.500 1.1311 0.06191 0.05894 -0.0034 0.0066 1.0000
13.750 1.1076 0.06895 0.06619 -0.0065 0.0066 1.0000
14.000 1.0811 0.07747 0.07492 -0.0113 0.0067 1.0000
14.250 1.0508 0.08811 0.08575 -0.0181 0.0068 1.0000
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