NACA 0012-64 a=0.8 c(li)=0.2 (naca001264a08cli02-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 0012-64 a=0.8 c(li)=0.2 (naca001264a08cli02-il) Reynolds number: 500,000 Max Cl/Cd: 63.35 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca001264a08cli02-il-500000-n5.txt Download as CSV file: xf-naca001264a08cli02-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0012-64 a=0.8 c(li)=0.2
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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4541 0.10198 0.09962 -0.0388 1.0000 0.0081
-10.250 -0.4575 0.09825 0.09591 -0.0396 1.0000 0.0081
-8.750 -0.4771 0.06480 0.06235 -0.0652 0.9857 0.0073
-8.500 -0.4756 0.06103 0.05848 -0.0662 0.9806 0.0071
-8.250 -0.4707 0.05653 0.05384 -0.0676 0.9771 0.0069
-8.000 -0.4674 0.05244 0.04958 -0.0671 0.9713 0.0068
-7.750 -0.4601 0.04824 0.04518 -0.0666 0.9669 0.0067
-7.500 -0.4521 0.04437 0.04108 -0.0653 0.9623 0.0066
-7.250 -0.4434 0.04076 0.03724 -0.0632 0.9568 0.0066
-7.000 -0.4312 0.03724 0.03343 -0.0614 0.9528 0.0066
-6.750 -0.4195 0.03399 0.02987 -0.0587 0.9477 0.0071
-6.500 -0.4061 0.03108 0.02665 -0.0560 0.9426 0.0072
-6.250 -0.3903 0.02849 0.02376 -0.0540 0.9389 0.0072
-6.000 -0.3732 0.02605 0.02102 -0.0519 0.9351 0.0071
-5.750 -0.3560 0.02371 0.01838 -0.0496 0.9301 0.0071
-5.500 -0.3354 0.02115 0.01547 -0.0476 0.9262 0.0073
-5.250 -0.3110 0.01800 0.01193 -0.0461 0.9235 0.0076
-5.000 -0.2872 0.01663 0.01039 -0.0454 0.9202 0.0079
-4.750 -0.2628 0.01589 0.00956 -0.0448 0.9161 0.0083
-4.500 -0.2373 0.01544 0.00904 -0.0445 0.9124 0.0089
-4.250 -0.2106 0.01452 0.00801 -0.0442 0.9094 0.0098
-4.000 -0.1854 0.01344 0.00682 -0.0435 0.9060 0.0103
-3.750 -0.1618 0.01272 0.00603 -0.0426 0.9016 0.0108
-3.500 -0.1395 0.01191 0.00517 -0.0415 0.8974 0.0115
-3.250 -0.1139 0.01155 0.00479 -0.0412 0.8940 0.0124
-3.000 -0.0887 0.01132 0.00455 -0.0407 0.8896 0.0138
-2.750 -0.0646 0.01096 0.00415 -0.0400 0.8849 0.0150
-2.500 -0.0401 0.01055 0.00368 -0.0393 0.8809 0.0161
-2.250 -0.0153 0.01019 0.00329 -0.0387 0.8768 0.0182
-2.000 0.0101 0.01002 0.00313 -0.0382 0.8712 0.0209
-1.750 0.0363 0.00981 0.00287 -0.0379 0.8659 0.0230
-1.500 0.0613 0.00958 0.00260 -0.0373 0.8587 0.0267
-1.250 0.0877 0.00943 0.00242 -0.0370 0.8518 0.0315
-1.000 0.1136 0.00930 0.00225 -0.0366 0.8449 0.0359
-0.750 0.1399 0.00917 0.00209 -0.0363 0.8389 0.0446
-0.500 0.1645 0.00887 0.00199 -0.0358 0.8331 0.1304
-0.250 0.1904 0.00874 0.00191 -0.0355 0.8265 0.1563
0.000 0.2161 0.00854 0.00180 -0.0352 0.8206 0.1890
0.250 0.2396 0.00823 0.00178 -0.0345 0.8132 0.2995
0.500 0.2562 0.00739 0.00166 -0.0325 0.8043 0.5259
0.750 0.2721 0.00684 0.00160 -0.0300 0.7921 0.6695
1.000 0.2905 0.00655 0.00156 -0.0278 0.7749 0.7595
1.500 0.3964 0.00673 0.00211 -0.0387 0.7276 0.9143
1.750 0.4156 0.00691 0.00217 -0.0367 0.7016 0.9294
2.000 0.4330 0.00713 0.00224 -0.0343 0.6633 0.9404
2.250 0.4471 0.00755 0.00238 -0.0312 0.5973 0.9524
2.500 0.4758 0.00830 0.00269 -0.0318 0.5036 0.9591
2.750 0.4995 0.00881 0.00295 -0.0311 0.4460 0.9662
3.000 0.5312 0.00942 0.00324 -0.0325 0.3703 0.9695
3.250 0.5542 0.01009 0.00353 -0.0320 0.2885 0.9734
3.500 0.5788 0.01059 0.00379 -0.0317 0.2370 0.9771
3.750 0.6126 0.01105 0.00406 -0.0336 0.1936 0.9792
4.000 0.6425 0.01143 0.00429 -0.0345 0.1612 0.9814
4.250 0.6702 0.01182 0.00454 -0.0349 0.1307 0.9842
4.500 0.6992 0.01220 0.00482 -0.0356 0.1075 0.9868
4.750 0.7344 0.01254 0.00508 -0.0378 0.0902 0.9887
5.000 0.7676 0.01286 0.00535 -0.0394 0.0768 0.9908
5.250 0.7987 0.01321 0.00565 -0.0406 0.0630 0.9932
5.500 0.8315 0.01361 0.00597 -0.0422 0.0491 0.9955
5.750 0.8675 0.01396 0.00630 -0.0445 0.0425 0.9976
6.000 0.8998 0.01428 0.00665 -0.0460 0.0401 0.9993
6.250 0.9256 0.01461 0.00701 -0.0460 0.0385 1.0000
6.500 0.9449 0.01494 0.00738 -0.0445 0.0373 1.0000
6.750 0.9636 0.01530 0.00777 -0.0429 0.0364 1.0000
7.000 0.9817 0.01569 0.00822 -0.0412 0.0356 1.0000
7.250 0.9987 0.01612 0.00871 -0.0393 0.0346 1.0000
7.500 1.0149 0.01660 0.00925 -0.0372 0.0339 1.0000
7.750 1.0301 0.01711 0.00983 -0.0350 0.0335 1.0000
8.000 1.0442 0.01766 0.01046 -0.0326 0.0331 1.0000
8.250 1.0591 0.01813 0.01100 -0.0303 0.0330 1.0000
8.500 1.0749 0.01849 0.01145 -0.0282 0.0327 1.0000
8.750 1.0915 0.01876 0.01178 -0.0263 0.0319 1.0000
9.000 1.1074 0.01903 0.01211 -0.0243 0.0306 1.0000
9.250 1.1213 0.01938 0.01253 -0.0219 0.0295 1.0000
9.500 1.1319 0.01973 0.01293 -0.0189 0.0286 1.0000
9.750 1.1414 0.02006 0.01331 -0.0156 0.0274 1.0000
10.000 1.1503 0.02046 0.01374 -0.0124 0.0262 1.0000
10.250 1.1573 0.02102 0.01436 -0.0088 0.0249 1.0000
10.500 1.1650 0.02159 0.01500 -0.0055 0.0239 1.0000
10.750 1.1792 0.02182 0.01533 -0.0034 0.0232 1.0000
11.000 1.1932 0.02208 0.01569 -0.0012 0.0217 1.0000
11.250 1.2074 0.02237 0.01604 0.0008 0.0186 1.0000
11.500 1.2201 0.02280 0.01641 0.0029 0.0138 1.0000
11.750 1.2288 0.02355 0.01713 0.0056 0.0103 1.0000
12.000 1.2354 0.02448 0.01811 0.0085 0.0086 1.0000
12.250 1.2422 0.02545 0.01916 0.0113 0.0076 1.0000
12.500 1.2493 0.02642 0.02025 0.0139 0.0070 1.0000
12.750 1.2554 0.02752 0.02146 0.0165 0.0064 1.0000
13.000 1.2605 0.02877 0.02282 0.0191 0.0059 1.0000
13.250 1.2637 0.03022 0.02442 0.0216 0.0055 1.0000
13.500 1.2696 0.03150 0.02583 0.0237 0.0052 1.0000
13.750 1.2743 0.03292 0.02740 0.0257 0.0049 1.0000
14.000 1.2779 0.03450 0.02911 0.0276 0.0047 1.0000
14.250 1.2802 0.03625 0.03100 0.0294 0.0044 1.0000
14.500 1.2809 0.03819 0.03309 0.0310 0.0042 1.0000
14.750 1.2796 0.04043 0.03547 0.0325 0.0040 1.0000
15.000 1.2756 0.04304 0.03822 0.0337 0.0039 1.0000
15.250 1.2687 0.04609 0.04143 0.0347 0.0038 1.0000
15.500 1.2590 0.04965 0.04515 0.0352 0.0037 1.0000
15.750 1.2520 0.05312 0.04879 0.0352 0.0036 1.0000
16.000 1.2424 0.05721 0.05305 0.0346 0.0036 1.0000
16.250 1.2303 0.06199 0.05800 0.0334 0.0035 1.0000
16.500 1.2153 0.06764 0.06383 0.0313 0.0035 1.0000
16.750 1.1965 0.07440 0.07077 0.0282 0.0035 1.0000
17.000 1.1730 0.08262 0.07917 0.0240 0.0035 1.0000
17.250 1.1414 0.09303 0.08979 0.0185 0.0036 1.0000
17.500 1.0992 0.10628 0.10323 0.0117 0.0037 1.0000
17.750 1.0650 0.11777 0.11490 0.0062 0.0038 1.0000
18.000 1.0246 0.13070 0.12799 0.0002 0.0041 1.0000
18.250 0.9803 0.14502 0.14244 -0.0067 0.0044 1.0000
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Polar data table (+)
Polar graphs
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