NACA 63-210 AIRFOIL (n63210-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 63-210 AIRFOIL (n63210-il) Reynolds number: 1,000,000 Max Cl/Cd: 66.35 at α=11° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n63210-il-1000000-n5.txt Download as CSV file: xf-n63210-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63-210 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -1.0246 0.05371 0.05159 -0.0403 1.0000 0.0030
-14.000 -1.0590 0.04551 0.04315 -0.0456 1.0000 0.0029
-13.750 -1.0802 0.04019 0.03763 -0.0479 1.0000 0.0029
-13.500 -1.0886 0.03696 0.03425 -0.0485 1.0000 0.0030
-13.250 -1.1008 0.03385 0.03094 -0.0480 1.0000 0.0029
-13.000 -1.1081 0.03162 0.02856 -0.0462 1.0000 0.0030
-12.750 -1.1096 0.02970 0.02647 -0.0443 1.0000 0.0031
-12.500 -1.1023 0.02792 0.02452 -0.0431 1.0000 0.0031
-12.250 -1.0918 0.02627 0.02270 -0.0421 1.0000 0.0032
-12.000 -1.0785 0.02478 0.02105 -0.0412 1.0000 0.0033
-11.750 -1.0632 0.02339 0.01949 -0.0405 1.0000 0.0034
-11.500 -1.0459 0.02218 0.01812 -0.0398 1.0000 0.0035
-11.250 -1.0272 0.02104 0.01685 -0.0392 1.0000 0.0036
-11.000 -1.0074 0.02004 0.01571 -0.0387 1.0000 0.0037
-10.750 -0.9865 0.01914 0.01468 -0.0382 1.0000 0.0037
-10.500 -0.9652 0.01827 0.01368 -0.0378 1.0000 0.0038
-10.250 -0.9430 0.01751 0.01282 -0.0373 1.0000 0.0039
-10.000 -0.9212 0.01663 0.01183 -0.0369 1.0000 0.0041
-9.750 -0.8986 0.01590 0.01100 -0.0364 1.0000 0.0044
-9.500 -0.8757 0.01523 0.01025 -0.0360 1.0000 0.0046
-9.250 -0.8529 0.01458 0.00954 -0.0355 1.0000 0.0050
-9.000 -0.8231 0.01394 0.00881 -0.0365 0.9932 0.0053
-8.750 -0.7920 0.01336 0.00816 -0.0377 0.9866 0.0058
-8.500 -0.7604 0.01300 0.00779 -0.0388 0.9801 0.0066
-8.000 -0.6970 0.01318 0.00809 -0.0407 0.9649 0.0104
-7.750 -0.6683 0.01326 0.00815 -0.0409 0.9548 0.0118
-7.500 -0.6403 0.01351 0.00838 -0.0409 0.9424 0.0123
-7.250 -0.6139 0.01368 0.00850 -0.0405 0.9214 0.0125
-7.000 -0.5931 0.01287 0.00751 -0.0394 0.8866 0.0131
-6.750 -0.5694 0.01237 0.00688 -0.0389 0.8693 0.0136
-6.500 -0.5437 0.01206 0.00651 -0.0387 0.8584 0.0141
-6.250 -0.5172 0.01187 0.00625 -0.0386 0.8500 0.0147
-6.000 -0.4902 0.01169 0.00605 -0.0386 0.8419 0.0155
-5.750 -0.4635 0.01140 0.00570 -0.0386 0.8346 0.0160
-5.500 -0.4368 0.01103 0.00526 -0.0385 0.8265 0.0161
-5.250 -0.4099 0.01069 0.00487 -0.0385 0.8187 0.0164
-5.000 -0.3828 0.01044 0.00456 -0.0385 0.8101 0.0168
-4.750 -0.3555 0.01012 0.00419 -0.0385 0.8014 0.0170
-4.500 -0.3284 0.00979 0.00379 -0.0385 0.7926 0.0169
-4.250 -0.3010 0.00948 0.00342 -0.0385 0.7831 0.0169
-4.000 -0.2734 0.00921 0.00308 -0.0386 0.7743 0.0168
-3.750 -0.2458 0.00898 0.00277 -0.0386 0.7653 0.0167
-3.500 -0.2179 0.00876 0.00251 -0.0387 0.7565 0.0167
-3.250 -0.1899 0.00858 0.00226 -0.0388 0.7482 0.0166
-3.000 -0.1618 0.00841 0.00204 -0.0388 0.7396 0.0166
-2.750 -0.1337 0.00826 0.00185 -0.0390 0.7315 0.0166
-2.500 -0.1055 0.00814 0.00168 -0.0391 0.7231 0.0166
-2.250 -0.0771 0.00802 0.00153 -0.0392 0.7147 0.0166
-2.000 -0.0489 0.00793 0.00140 -0.0393 0.7065 0.0166
-1.750 -0.0204 0.00784 0.00129 -0.0394 0.6980 0.0167
-1.500 0.0080 0.00777 0.00119 -0.0395 0.6900 0.0168
-1.250 0.0364 0.00771 0.00110 -0.0397 0.6813 0.0170
-1.000 0.0648 0.00765 0.00103 -0.0398 0.6732 0.0175
-0.750 0.0932 0.00761 0.00097 -0.0399 0.6647 0.0181
-0.500 0.1216 0.00758 0.00093 -0.0401 0.6527 0.0229
-0.250 0.1482 0.00622 0.00067 -0.0410 0.6240 0.4133
0.000 0.1758 0.00593 0.00066 -0.0412 0.6004 0.5178
0.250 0.2038 0.00593 0.00071 -0.0414 0.5781 0.5651
0.500 0.2319 0.00604 0.00074 -0.0414 0.5516 0.5785
0.750 0.2596 0.00620 0.00077 -0.0415 0.5132 0.5876
1.000 0.2863 0.00651 0.00084 -0.0414 0.4443 0.5987
1.250 0.3108 0.00721 0.00105 -0.0413 0.3031 0.6159
1.500 0.3317 0.00867 0.00155 -0.0408 0.0207 0.6344
1.750 0.3598 0.00874 0.00165 -0.0409 0.0192 0.6457
2.000 0.3878 0.00883 0.00177 -0.0410 0.0183 0.6568
2.250 0.4158 0.00893 0.00190 -0.0411 0.0176 0.6710
2.500 0.4437 0.00903 0.00203 -0.0411 0.0171 0.6855
2.750 0.4715 0.00915 0.00219 -0.0412 0.0167 0.6986
3.000 0.4993 0.00928 0.00237 -0.0412 0.0163 0.7107
3.250 0.5269 0.00943 0.00255 -0.0412 0.0159 0.7221
3.500 0.5544 0.00960 0.00277 -0.0412 0.0154 0.7333
3.750 0.5817 0.00980 0.00304 -0.0411 0.0149 0.7441
4.000 0.6086 0.01006 0.00337 -0.0410 0.0143 0.7546
4.250 0.6349 0.01042 0.00381 -0.0408 0.0138 0.7658
4.500 0.6617 0.01068 0.00412 -0.0407 0.0137 0.7776
4.750 0.6881 0.01096 0.00448 -0.0405 0.0137 0.7886
5.000 0.7143 0.01128 0.00486 -0.0403 0.0136 0.7989
5.250 0.7402 0.01163 0.00527 -0.0400 0.0135 0.8094
5.750 0.7907 0.01246 0.00625 -0.0393 0.0135 0.8323
6.000 0.8152 0.01292 0.00681 -0.0389 0.0134 0.8448
6.250 0.8391 0.01343 0.00742 -0.0383 0.0134 0.8589
6.500 0.8622 0.01398 0.00807 -0.0375 0.0134 0.8756
6.750 0.8859 0.01437 0.00855 -0.0369 0.0133 0.8913
7.000 0.9104 0.01451 0.00874 -0.0364 0.0129 0.9075
7.250 0.9338 0.01474 0.00905 -0.0356 0.0125 0.9242
7.500 0.9551 0.01517 0.00956 -0.0345 0.0123 0.9434
8.000 1.0044 0.01596 0.01047 -0.0339 0.0116 1.0000
8.250 1.0300 0.01623 0.01075 -0.0338 0.0110 1.0000
8.500 1.0543 0.01668 0.01124 -0.0335 0.0108 1.0000
8.750 1.0789 0.01703 0.01163 -0.0332 0.0104 1.0000
9.000 1.1039 0.01729 0.01189 -0.0331 0.0101 1.0000
9.250 1.1286 0.01757 0.01218 -0.0329 0.0097 1.0000
9.500 1.1512 0.01812 0.01275 -0.0324 0.0093 1.0000
9.750 1.1751 0.01847 0.01313 -0.0321 0.0091 1.0000
10.000 1.2005 0.01863 0.01332 -0.0319 0.0088 1.0000
10.250 1.2240 0.01903 0.01380 -0.0315 0.0081 1.0000
10.500 1.2385 0.02067 0.01571 -0.0299 0.0059 1.0000
10.750 1.2717 0.01959 0.01442 -0.0309 0.0055 1.0000
11.000 1.2978 0.01956 0.01426 -0.0309 0.0049 1.0000
11.250 1.3192 0.02007 0.01477 -0.0303 0.0043 1.0000
11.500 1.3377 0.02085 0.01563 -0.0293 0.0040 1.0000
11.750 1.3549 0.02171 0.01659 -0.0281 0.0038 1.0000
12.000 1.3705 0.02264 0.01763 -0.0268 0.0036 1.0000
12.250 1.3850 0.02360 0.01871 -0.0254 0.0035 1.0000
12.500 1.3955 0.02461 0.01982 -0.0233 0.0033 1.0000
12.750 1.4027 0.02573 0.02106 -0.0209 0.0032 1.0000
13.000 1.4097 0.02689 0.02233 -0.0187 0.0031 1.0000
13.250 1.4151 0.02824 0.02380 -0.0166 0.0030 1.0000
13.500 1.4203 0.02967 0.02534 -0.0148 0.0029 1.0000
13.750 1.4223 0.03147 0.02728 -0.0131 0.0027 1.0000
14.000 1.4244 0.03337 0.02931 -0.0117 0.0026 1.0000
14.250 1.4249 0.03552 0.03159 -0.0106 0.0025 1.0000
14.500 1.4242 0.03788 0.03409 -0.0098 0.0025 1.0000
14.750 1.4217 0.04060 0.03696 -0.0093 0.0024 1.0000
15.000 1.4184 0.04356 0.04006 -0.0091 0.0024 1.0000
15.250 1.4134 0.04689 0.04356 -0.0094 0.0024 1.0000
15.500 1.4068 0.05062 0.04743 -0.0101 0.0024 1.0000
15.750 1.3992 0.05472 0.05168 -0.0114 0.0024 1.0000
16.000 1.3875 0.05967 0.05678 -0.0133 0.0024 1.0000
16.250 1.3725 0.06547 0.06275 -0.0159 0.0024 1.0000
16.500 1.3528 0.07254 0.06999 -0.0196 0.0024 1.0000
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Polar data table (+)
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