NACA 0012-64 a=0.8 c(li)=0.2 (naca001264a08cli02-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 0012-64 a=0.8 c(li)=0.2 (naca001264a08cli02-il) Reynolds number: 50,000 Max Cl/Cd: 32.21 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca001264a08cli02-il-50000-n5.txt Download as CSV file: xf-naca001264a08cli02-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-6.500 -0.6037 0.06374 0.05641 -0.0197 1.0000 0.0799
-6.250 -0.5988 0.06010 0.05239 -0.0168 1.0000 0.0673
-6.000 -0.5937 0.05775 0.04927 -0.0127 1.0000 0.0569
-5.750 -0.5832 0.05379 0.04544 -0.0111 1.0000 0.0540
-5.500 -0.5744 0.05084 0.04221 -0.0085 1.0000 0.0512
-5.250 -0.5640 0.04811 0.03907 -0.0058 1.0000 0.0492
-5.000 -0.5515 0.04567 0.03619 -0.0032 1.0000 0.0483
-4.750 -0.5371 0.04340 0.03351 -0.0009 1.0000 0.0480
-4.500 -0.5205 0.04130 0.03095 0.0013 1.0000 0.0476
-4.250 -0.5018 0.03967 0.02876 0.0036 1.0000 0.0464
-4.000 -0.4821 0.03861 0.02719 0.0057 1.0000 0.0454
-3.750 -0.4606 0.03693 0.02516 0.0071 1.0000 0.0450
-3.500 -0.4377 0.03523 0.02317 0.0082 1.0000 0.0450
-3.250 -0.4133 0.03318 0.02097 0.0088 1.0000 0.0463
-3.000 -0.3883 0.03150 0.01924 0.0092 1.0000 0.0490
-2.750 -0.3629 0.03037 0.01797 0.0100 1.0000 0.0508
-2.500 -0.3371 0.02945 0.01688 0.0107 1.0000 0.0520
-2.250 -0.3071 0.02868 0.01591 0.0104 0.9985 0.0541
-2.000 -0.2732 0.02791 0.01490 0.0091 0.9953 0.0591
-1.750 -0.2420 0.02721 0.01402 0.0081 0.9915 0.0634
-1.500 -0.2093 0.02683 0.01339 0.0069 0.9874 0.0690
-1.000 -0.0665 0.02405 0.01401 -0.0094 0.9957 1.0000
-0.750 -0.0336 0.02431 0.01392 -0.0111 0.9896 1.0000
-0.500 -0.0008 0.02460 0.01390 -0.0129 0.9833 1.0000
-0.250 0.0328 0.02491 0.01396 -0.0148 0.9770 1.0000
0.000 0.0636 0.02517 0.01401 -0.0162 0.9695 1.0000
0.250 0.0967 0.02549 0.01415 -0.0181 0.9627 1.0000
0.500 0.1277 0.02577 0.01431 -0.0194 0.9549 1.0000
0.750 0.1582 0.02607 0.01450 -0.0207 0.9473 1.0000
1.000 0.1900 0.02638 0.01473 -0.0222 0.9397 1.0000
1.250 0.2185 0.02668 0.01498 -0.0230 0.9313 1.0000
1.500 0.2523 0.02699 0.01526 -0.0248 0.9240 1.0000
1.750 0.2780 0.02728 0.01555 -0.0251 0.9144 1.0000
2.000 0.3156 0.02758 0.01587 -0.0275 0.9077 1.0000
2.250 0.3391 0.02785 0.01618 -0.0272 0.8968 1.0000
2.500 0.3674 0.02812 0.01650 -0.0278 0.8868 1.0000
2.750 0.4063 0.02830 0.01680 -0.0303 0.8787 1.0000
3.000 0.4334 0.02846 0.01706 -0.0304 0.8662 1.0000
3.250 0.4673 0.02842 0.01715 -0.0315 0.8523 1.0000
3.500 0.5121 0.02795 0.01688 -0.0339 0.8362 1.0000
3.750 0.5397 0.02762 0.01669 -0.0332 0.8154 1.0000
4.000 0.5769 0.02705 0.01633 -0.0340 0.7970 1.0000
4.250 0.6152 0.02635 0.01588 -0.0347 0.7786 1.0000
4.500 0.6400 0.02587 0.01558 -0.0330 0.7539 1.0000
4.750 0.6694 0.02507 0.01497 -0.0315 0.7228 1.0000
5.000 0.6943 0.02445 0.01453 -0.0294 0.6826 1.0000
5.250 0.7183 0.02397 0.01414 -0.0271 0.6295 1.0000
5.500 0.7519 0.02345 0.01342 -0.0261 0.5401 1.0000
5.750 0.7718 0.02396 0.01336 -0.0235 0.4273 1.0000
6.000 0.7767 0.02520 0.01396 -0.0194 0.3346 1.0000
6.250 0.7803 0.02661 0.01484 -0.0155 0.2687 1.0000
6.500 0.7873 0.02795 0.01584 -0.0123 0.2213 1.0000
6.750 0.7972 0.02918 0.01687 -0.0097 0.1869 1.0000
7.000 0.8094 0.03038 0.01797 -0.0074 0.1627 1.0000
7.250 0.8248 0.03156 0.01915 -0.0055 0.1451 1.0000
7.500 0.8426 0.03275 0.02035 -0.0041 0.1306 1.0000
7.750 0.8623 0.03392 0.02156 -0.0030 0.1181 1.0000
8.000 0.8827 0.03514 0.02274 -0.0021 0.1088 1.0000
8.250 0.9121 0.03653 0.02446 -0.0023 0.1015 1.0000
8.500 0.9401 0.03808 0.02608 -0.0026 0.0965 1.0000
8.750 0.9708 0.04001 0.02827 -0.0031 0.0927 1.0000
9.000 0.9964 0.04209 0.03074 -0.0029 0.0895 1.0000
9.250 1.0177 0.04430 0.03328 -0.0021 0.0869 1.0000
9.500 1.0357 0.04662 0.03596 -0.0009 0.0849 1.0000
9.750 1.0515 0.04882 0.03832 0.0003 0.0822 1.0000
10.000 1.0564 0.05128 0.04118 0.0032 0.0796 1.0000
10.250 1.0554 0.05383 0.04422 0.0068 0.0771 1.0000
10.500 1.0534 0.05673 0.04753 0.0103 0.0756 1.0000
10.750 1.0472 0.05974 0.05090 0.0140 0.0745 1.0000
11.000 1.0365 0.06277 0.05424 0.0180 0.0737 1.0000
11.250 1.0210 0.06569 0.05742 0.0222 0.0730 1.0000
11.500 1.0040 0.06875 0.06070 0.0259 0.0722 1.0000
11.750 0.9868 0.07203 0.06416 0.0287 0.0713 1.0000
12.000 1.0002 0.07390 0.06592 0.0294 0.0677 1.0000
12.250 0.9744 0.07793 0.07017 0.0317 0.0676 1.0000
12.500 0.9483 0.08258 0.07501 0.0326 0.0676 1.0000
12.750 0.9222 0.08793 0.08050 0.0322 0.0677 1.0000
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Polar data table (+)
Polar graphs
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