NACA 64A210 (naca64a210-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 64A210 (naca64a210-il) Reynolds number: 1,000,000 Max Cl/Cd: 73.18 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca64a210-il-1000000-n5.txt Download as CSV file: xf-naca64a210-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -1.0383 0.04718 0.04513 -0.0468 1.0000 0.0040
-13.500 -1.0663 0.04041 0.03809 -0.0506 1.0000 0.0040
-13.250 -1.0797 0.03653 0.03399 -0.0510 1.0000 0.0041
-13.000 -1.0857 0.03383 0.03109 -0.0497 1.0000 0.0041
-12.750 -1.0825 0.03152 0.02859 -0.0486 1.0000 0.0042
-12.500 -1.0744 0.02951 0.02639 -0.0477 1.0000 0.0043
-12.250 -1.0633 0.02772 0.02441 -0.0468 1.0000 0.0044
-12.000 -1.0500 0.02612 0.02263 -0.0459 1.0000 0.0046
-11.750 -1.0351 0.02466 0.02100 -0.0450 1.0000 0.0047
-11.500 -1.0187 0.02338 0.01956 -0.0441 1.0000 0.0048
-11.250 -1.0011 0.02227 0.01830 -0.0433 1.0000 0.0050
-11.000 -0.9828 0.02130 0.01718 -0.0424 1.0000 0.0051
-10.750 -0.9643 0.02042 0.01619 -0.0413 1.0000 0.0052
-10.500 -0.9488 0.01927 0.01489 -0.0399 1.0000 0.0055
-10.250 -0.9283 0.01863 0.01420 -0.0391 0.9995 0.0057
-10.000 -0.8990 0.01803 0.01353 -0.0401 0.9970 0.0059
-9.750 -0.8691 0.01740 0.01282 -0.0412 0.9946 0.0062
-9.500 -0.8408 0.01676 0.01210 -0.0419 0.9909 0.0065
-9.250 -0.8115 0.01611 0.01135 -0.0428 0.9873 0.0068
-9.000 -0.7828 0.01546 0.01059 -0.0436 0.9831 0.0071
-8.750 -0.7542 0.01487 0.00991 -0.0443 0.9782 0.0074
-8.500 -0.7254 0.01436 0.00932 -0.0449 0.9731 0.0076
-8.250 -0.6989 0.01363 0.00849 -0.0451 0.9663 0.0080
-8.000 -0.6722 0.01314 0.00796 -0.0453 0.9595 0.0085
-7.750 -0.6454 0.01284 0.00761 -0.0453 0.9521 0.0089
-7.500 -0.6193 0.01253 0.00725 -0.0452 0.9444 0.0094
-7.250 -0.5938 0.01215 0.00681 -0.0449 0.9363 0.0098
-7.000 -0.5683 0.01177 0.00635 -0.0446 0.9281 0.0102
-6.750 -0.5428 0.01142 0.00592 -0.0443 0.9204 0.0106
-6.500 -0.5169 0.01110 0.00554 -0.0441 0.9123 0.0109
-6.250 -0.4909 0.01083 0.00519 -0.0439 0.9048 0.0111
-6.000 -0.4660 0.01026 0.00454 -0.0435 0.8967 0.0120
-5.750 -0.4399 0.00994 0.00417 -0.0433 0.8894 0.0126
-5.500 -0.4135 0.00967 0.00385 -0.0431 0.8818 0.0131
-5.250 -0.3869 0.00942 0.00354 -0.0430 0.8746 0.0137
-5.000 -0.3601 0.00920 0.00327 -0.0429 0.8670 0.0145
-4.750 -0.3331 0.00900 0.00302 -0.0428 0.8599 0.0152
-4.500 -0.3061 0.00881 0.00278 -0.0427 0.8521 0.0156
-4.250 -0.2792 0.00856 0.00246 -0.0426 0.8447 0.0170
-4.000 -0.2522 0.00837 0.00225 -0.0425 0.8365 0.0189
-3.750 -0.2249 0.00821 0.00207 -0.0425 0.8284 0.0210
-3.500 -0.1976 0.00807 0.00189 -0.0424 0.8197 0.0243
-3.250 -0.1703 0.00792 0.00173 -0.0424 0.8101 0.0301
-3.000 -0.1431 0.00776 0.00159 -0.0423 0.8009 0.0401
-2.750 -0.1160 0.00761 0.00145 -0.0423 0.7911 0.0552
-2.500 -0.0889 0.00743 0.00133 -0.0422 0.7809 0.0793
-2.250 -0.0621 0.00720 0.00119 -0.0422 0.7716 0.1211
-2.000 -0.0363 0.00679 0.00105 -0.0421 0.7626 0.2095
-1.750 -0.0115 0.00618 0.00088 -0.0419 0.7531 0.3483
-1.500 0.0137 0.00574 0.00079 -0.0417 0.7441 0.4646
-1.250 0.0406 0.00559 0.00075 -0.0416 0.7351 0.5152
-1.000 0.0674 0.00543 0.00074 -0.0415 0.7265 0.5692
-0.750 0.0942 0.00532 0.00074 -0.0413 0.7179 0.6160
-0.500 0.1216 0.00527 0.00074 -0.0412 0.7086 0.6419
-0.250 0.1493 0.00525 0.00075 -0.0412 0.7000 0.6594
0.250 0.2051 0.00526 0.00076 -0.0413 0.6829 0.6813
0.500 0.2330 0.00529 0.00078 -0.0413 0.6744 0.6898
0.750 0.2609 0.00531 0.00080 -0.0414 0.6653 0.6992
1.000 0.2885 0.00535 0.00084 -0.0414 0.6525 0.7082
1.500 0.3429 0.00550 0.00091 -0.0412 0.6140 0.7266
1.750 0.3696 0.00562 0.00097 -0.0410 0.5856 0.7360
2.000 0.3956 0.00583 0.00104 -0.0407 0.5439 0.7460
2.250 0.4212 0.00607 0.00113 -0.0404 0.4945 0.7554
2.500 0.4456 0.00647 0.00127 -0.0399 0.4199 0.7650
3.000 0.4907 0.00782 0.00183 -0.0386 0.2063 0.7864
3.250 0.5137 0.00845 0.00211 -0.0380 0.1162 0.7972
3.500 0.5389 0.00878 0.00233 -0.0377 0.0776 0.8092
3.750 0.5646 0.00900 0.00253 -0.0374 0.0566 0.8240
4.000 0.5899 0.00920 0.00273 -0.0371 0.0411 0.8435
4.250 0.6147 0.00934 0.00293 -0.0365 0.0321 0.8733
4.500 0.6385 0.00943 0.00315 -0.0356 0.0262 0.9212
4.750 0.6708 0.00965 0.00341 -0.0367 0.0204 0.9675
5.000 0.7057 0.00993 0.00367 -0.0386 0.0169 0.9936
5.250 0.7335 0.01023 0.00397 -0.0388 0.0146 1.0000
5.500 0.7587 0.01048 0.00424 -0.0384 0.0138 1.0000
5.750 0.7839 0.01076 0.00454 -0.0380 0.0130 1.0000
6.000 0.8088 0.01106 0.00485 -0.0376 0.0123 1.0000
6.250 0.8335 0.01139 0.00520 -0.0372 0.0118 1.0000
6.500 0.8580 0.01176 0.00559 -0.0368 0.0113 1.0000
6.750 0.8819 0.01219 0.00607 -0.0362 0.0109 1.0000
7.000 0.9050 0.01273 0.00666 -0.0355 0.0105 1.0000
7.250 0.9281 0.01326 0.00725 -0.0349 0.0102 1.0000
7.500 0.9523 0.01363 0.00766 -0.0344 0.0101 1.0000
7.750 0.9763 0.01402 0.00809 -0.0340 0.0098 1.0000
8.000 0.9997 0.01448 0.00860 -0.0334 0.0096 1.0000
8.250 1.0228 0.01498 0.00916 -0.0328 0.0093 1.0000
8.500 1.0455 0.01550 0.00973 -0.0322 0.0090 1.0000
8.750 1.0682 0.01601 0.01029 -0.0316 0.0087 1.0000
9.000 1.0911 0.01648 0.01080 -0.0310 0.0083 1.0000
9.250 1.1140 0.01693 0.01128 -0.0305 0.0080 1.0000
9.500 1.1358 0.01748 0.01187 -0.0298 0.0077 1.0000
9.750 1.1558 0.01825 0.01272 -0.0289 0.0074 1.0000
10.000 1.1720 0.01946 0.01405 -0.0274 0.0070 1.0000
10.250 1.1928 0.02005 0.01471 -0.0266 0.0069 1.0000
10.500 1.2131 0.02067 0.01542 -0.0258 0.0068 1.0000
10.750 1.2325 0.02136 0.01620 -0.0248 0.0067 1.0000
11.000 1.2514 0.02206 0.01698 -0.0238 0.0065 1.0000
11.250 1.2698 0.02276 0.01776 -0.0228 0.0062 1.0000
11.500 1.2875 0.02344 0.01852 -0.0217 0.0060 1.0000
11.750 1.3038 0.02410 0.01927 -0.0203 0.0057 1.0000
12.000 1.3191 0.02478 0.02002 -0.0188 0.0055 1.0000
12.250 1.3336 0.02550 0.02080 -0.0174 0.0053 1.0000
12.500 1.3470 0.02629 0.02166 -0.0158 0.0052 1.0000
12.750 1.3596 0.02715 0.02259 -0.0143 0.0051 1.0000
13.000 1.3704 0.02817 0.02368 -0.0127 0.0049 1.0000
13.250 1.3781 0.02948 0.02509 -0.0110 0.0048 1.0000
13.500 1.3823 0.03115 0.02690 -0.0091 0.0046 1.0000
13.750 1.3884 0.03270 0.02857 -0.0077 0.0046 1.0000
14.000 1.3934 0.03438 0.03039 -0.0063 0.0045 1.0000
14.250 1.3965 0.03633 0.03249 -0.0051 0.0044 1.0000
14.500 1.3985 0.03844 0.03473 -0.0041 0.0043 1.0000
14.750 1.3985 0.04086 0.03729 -0.0033 0.0043 1.0000
15.000 1.3964 0.04361 0.04019 -0.0028 0.0042 1.0000
15.250 1.3930 0.04667 0.04339 -0.0026 0.0041 1.0000
15.500 1.3880 0.05006 0.04692 -0.0029 0.0040 1.0000
15.750 1.3801 0.05400 0.05101 -0.0035 0.0040 1.0000
16.000 1.3691 0.05861 0.05578 -0.0048 0.0039 1.0000
16.250 1.3560 0.06377 0.06109 -0.0066 0.0039 1.0000
16.500 1.3372 0.07027 0.06776 -0.0094 0.0039 1.0000
16.750 1.3129 0.07823 0.07589 -0.0134 0.0039 1.0000
17.000 1.2798 0.08874 0.08661 -0.0193 0.0039 1.0000
17.250 1.2145 0.10776 0.10592 -0.0303 0.0041 1.0000
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