NACA 64-210 (naca64210-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 64-210 (naca64210-il) Reynolds number: 1,000,000 Max Cl/Cd: 85.73 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca64210-il-1000000.txt Download as CSV file: xf-naca64210-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64-210
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
------ -------- --------- --------- -------- -------- --------
-11.500 -0.4820 0.10340 0.10186 -0.0134 1.0000 0.0125
-11.250 -0.4806 0.09944 0.09790 -0.0149 1.0000 0.0127
-11.000 -0.6490 0.04728 0.04569 -0.0390 1.0000 0.0088
-10.750 -0.6411 0.04610 0.04449 -0.0408 1.0000 0.0089
-10.500 -0.6221 0.04768 0.04610 -0.0411 1.0000 0.0091
-10.250 -0.6224 0.04558 0.04396 -0.0430 1.0000 0.0092
-10.000 -0.7614 0.04400 0.04192 -0.0453 1.0000 0.0083
-9.750 -0.7926 0.01828 0.01543 -0.0419 1.0000 0.0086
-9.500 -0.7942 0.01441 0.01122 -0.0405 1.0000 0.0090
-9.250 -0.7736 0.01419 0.01099 -0.0402 1.0000 0.0093
-9.000 -0.7582 0.01274 0.00938 -0.0394 1.0000 0.0095
-8.750 -0.7423 0.01125 0.00770 -0.0386 1.0000 0.0098
-8.500 -0.7250 0.01006 0.00636 -0.0377 1.0000 0.0101
-8.250 -0.7102 0.00854 0.00463 -0.0363 1.0000 0.0105
-8.000 -0.6834 0.00710 0.00295 -0.0372 0.9961 0.0109
-7.750 -0.6540 0.00597 0.00163 -0.0385 0.9907 0.0114
-7.500 -0.6219 0.00543 0.00095 -0.0399 0.9850 0.0118
-7.250 -0.6249 0.01435 0.00940 -0.0385 0.9868 0.0125
-7.000 -0.5911 0.01370 0.00873 -0.0403 0.9825 0.0132
-6.750 -0.5589 0.01320 0.00820 -0.0416 0.9749 0.0139
-6.500 -0.5268 0.01255 0.00747 -0.0428 0.9668 0.0146
-6.250 -0.4974 0.01193 0.00677 -0.0434 0.9559 0.0152
-6.000 -0.4713 0.01149 0.00626 -0.0431 0.9428 0.0158
-5.750 -0.4456 0.01121 0.00590 -0.0427 0.9300 0.0162
-5.500 -0.4232 0.01020 0.00477 -0.0420 0.9173 0.0177
-5.250 -0.3977 0.00986 0.00438 -0.0416 0.9061 0.0187
-5.000 -0.3718 0.00957 0.00402 -0.0413 0.8954 0.0197
-4.750 -0.3456 0.00930 0.00368 -0.0410 0.8849 0.0209
-4.500 -0.3187 0.00909 0.00342 -0.0408 0.8747 0.0220
-4.250 -0.2926 0.00862 0.00285 -0.0406 0.8649 0.0247
-4.000 -0.2657 0.00841 0.00261 -0.0405 0.8553 0.0276
-3.750 -0.2382 0.00826 0.00241 -0.0404 0.8459 0.0301
-3.500 -0.2111 0.00797 0.00208 -0.0403 0.8369 0.0364
-3.250 -0.1836 0.00780 0.00187 -0.0403 0.8274 0.0429
-3.000 -0.1564 0.00747 0.00166 -0.0403 0.8181 0.0774
-2.750 -0.1304 0.00678 0.00140 -0.0405 0.8091 0.2043
-2.500 -0.1052 0.00578 0.00111 -0.0408 0.7998 0.4105
-2.250 -0.0781 0.00542 0.00103 -0.0409 0.7912 0.5099
-2.000 -0.0504 0.00530 0.00098 -0.0409 0.7824 0.5510
-1.750 -0.0222 0.00522 0.00094 -0.0410 0.7734 0.5771
-1.500 0.0059 0.00518 0.00090 -0.0410 0.7647 0.5970
-1.250 0.0340 0.00513 0.00089 -0.0411 0.7554 0.6224
-1.000 0.0619 0.00507 0.00090 -0.0411 0.7467 0.6557
-0.750 0.0898 0.00506 0.00091 -0.0411 0.7382 0.6785
-0.500 0.1182 0.00505 0.00091 -0.0412 0.7294 0.6899
-0.250 0.1466 0.00506 0.00091 -0.0412 0.7212 0.7004
0.000 0.1749 0.00507 0.00091 -0.0413 0.7123 0.7098
0.250 0.2033 0.00508 0.00093 -0.0414 0.7039 0.7186
0.500 0.2315 0.00511 0.00094 -0.0415 0.6952 0.7280
0.750 0.2598 0.00512 0.00097 -0.0416 0.6854 0.7372
1.000 0.2880 0.00514 0.00099 -0.0417 0.6755 0.7462
1.250 0.3161 0.00519 0.00103 -0.0417 0.6640 0.7558
1.500 0.3438 0.00523 0.00106 -0.0416 0.6446 0.7651
1.750 0.3712 0.00532 0.00109 -0.0415 0.6207 0.7748
2.000 0.3989 0.00540 0.00114 -0.0415 0.5983 0.7848
2.250 0.4263 0.00549 0.00121 -0.0414 0.5767 0.7942
2.500 0.4538 0.00559 0.00128 -0.0414 0.5547 0.8037
2.750 0.4813 0.00570 0.00136 -0.0413 0.5322 0.8137
3.000 0.5075 0.00592 0.00148 -0.0411 0.4870 0.8235
3.250 0.5310 0.00656 0.00170 -0.0405 0.3730 0.8337
3.500 0.5521 0.00759 0.00213 -0.0398 0.2228 0.8447
3.750 0.5742 0.00844 0.00252 -0.0392 0.1103 0.8558
4.000 0.5981 0.00900 0.00286 -0.0387 0.0520 0.8666
4.250 0.6235 0.00931 0.00313 -0.0383 0.0380 0.8779
4.500 0.6490 0.00955 0.00341 -0.0379 0.0319 0.8901
4.750 0.6737 0.00985 0.00373 -0.0373 0.0268 0.9031
5.000 0.6979 0.01014 0.00411 -0.0366 0.0237 0.9169
5.250 0.7215 0.01036 0.00438 -0.0357 0.0216 0.9322
5.500 0.7433 0.01065 0.00471 -0.0345 0.0194 0.9520
5.750 0.7700 0.01119 0.00535 -0.0344 0.0177 0.9831
6.000 0.7981 0.01154 0.00574 -0.0348 0.0170 1.0000
6.250 0.8240 0.01197 0.00621 -0.0346 0.0161 1.0000
6.500 0.8494 0.01243 0.00670 -0.0344 0.0154 1.0000
6.750 0.8744 0.01292 0.00721 -0.0341 0.0148 1.0000
7.000 0.8986 0.01349 0.00781 -0.0337 0.0142 1.0000
7.250 0.9171 0.01493 0.00935 -0.0325 0.0132 1.0000
7.500 0.9411 0.01554 0.01002 -0.0321 0.0128 1.0000
7.750 0.9650 0.01616 0.01070 -0.0316 0.0125 1.0000
8.000 0.9882 0.01691 0.01152 -0.0311 0.0121 1.0000
8.250 1.0108 0.01776 0.01246 -0.0304 0.0117 1.0000
8.500 1.0332 0.01864 0.01342 -0.0298 0.0114 1.0000
8.750 1.0553 0.01955 0.01441 -0.0292 0.0110 1.0000
9.000 1.0776 0.02029 0.01523 -0.0286 0.0106 1.0000
9.250 1.0999 0.02083 0.01579 -0.0282 0.0102 1.0000
9.500 1.1200 0.02180 0.01683 -0.0274 0.0099 1.0000
9.750 1.1282 0.02588 0.02129 -0.0254 0.0093 1.0000
10.000 1.1478 0.02660 0.02215 -0.0245 0.0091 1.0000
10.250 1.1649 0.02778 0.02349 -0.0234 0.0089 1.0000
10.500 1.1791 0.02934 0.02523 -0.0220 0.0087 1.0000
10.750 1.1888 0.03143 0.02756 -0.0202 0.0084 1.0000
11.000 1.1933 0.03393 0.03032 -0.0180 0.0082 1.0000
11.250 1.1895 0.03673 0.03338 -0.0149 0.0081 1.0000
11.500 1.1801 0.03924 0.03611 -0.0112 0.0079 1.0000
11.750 1.1675 0.04212 0.03920 -0.0082 0.0079 1.0000
12.000 1.1399 0.04697 0.04435 -0.0057 0.0078 1.0000
12.250 1.1232 0.05089 0.04845 -0.0050 0.0077 1.0000
12.500 1.0678 0.06087 0.05880 -0.0067 0.0079 1.0000
12.750 1.0312 0.06962 0.06778 -0.0107 0.0079 1.0000
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Polar data table (+)
Polar graphs
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