NACA 0010-34 a=0.8 c(li)=0.2 (naca001034a08cli02-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 0010-34 a=0.8 c(li)=0.2 (naca001034a08cli02-il) Reynolds number: 100,000 Max Cl/Cd: 47.27 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca001034a08cli02-il-100000.txt Download as CSV file: xf-naca001034a08cli02-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0010-34 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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5485 0.09963 0.09490 -0.0444 1.0000 0.0881
-9.250 -0.5696 0.09625 0.09154 -0.0461 1.0000 0.0882
-9.000 -0.5928 0.09369 0.08897 -0.0455 1.0000 0.0883
-8.750 -0.5208 0.08955 0.08483 -0.0362 1.0000 0.1088
-8.500 -0.5362 0.08567 0.08105 -0.0384 1.0000 0.1115
-8.250 -0.5584 0.08231 0.07782 -0.0387 1.0000 0.1122
-8.000 -0.5817 0.07904 0.07455 -0.0387 1.0000 0.1135
-7.750 -0.6077 0.07642 0.07181 -0.0376 1.0000 0.1145
-7.500 -0.5926 0.07282 0.06833 -0.0346 1.0000 0.1241
-7.250 -0.6218 0.07060 0.06589 -0.0333 1.0000 0.1281
-4.750 -0.5289 0.03298 0.02498 -0.0144 1.0000 0.0697
-4.500 -0.5035 0.03027 0.02161 -0.0124 1.0000 0.0589
-4.250 -0.4787 0.02768 0.01863 -0.0112 1.0000 0.0549
-4.000 -0.4538 0.02596 0.01659 -0.0102 1.0000 0.0564
-3.750 -0.4280 0.02444 0.01481 -0.0093 1.0000 0.0585
-3.500 -0.4015 0.02287 0.01303 -0.0085 1.0000 0.0589
-3.250 -0.3764 0.02162 0.01169 -0.0075 1.0000 0.0608
-3.000 -0.3534 0.02021 0.01035 -0.0066 1.0000 0.0652
-2.750 -0.3308 0.01930 0.00944 -0.0058 1.0000 0.0778
-2.500 -0.1662 0.01697 0.01038 -0.0230 1.0000 0.9948
-2.250 -0.1449 0.01665 0.00983 -0.0237 1.0000 1.0000
-2.000 -0.1510 0.01630 0.00938 -0.0191 1.0000 1.0000
-1.750 -0.1538 0.01603 0.00900 -0.0149 1.0000 1.0000
-1.500 -0.1511 0.01587 0.00870 -0.0114 1.0000 1.0000
-1.250 -0.1435 0.01583 0.00850 -0.0087 1.0000 1.0000
-1.000 -0.1318 0.01587 0.00836 -0.0066 1.0000 1.0000
-0.750 -0.1171 0.01599 0.00834 -0.0050 1.0000 1.0000
-0.500 -0.1006 0.01617 0.00838 -0.0038 1.0000 1.0000
-0.250 -0.0829 0.01640 0.00849 -0.0029 1.0000 1.0000
0.000 -0.0645 0.01666 0.00866 -0.0021 1.0000 1.0000
0.250 -0.0456 0.01697 0.00886 -0.0014 1.0000 1.0000
0.500 -0.0192 0.01737 0.00918 -0.0023 0.9979 1.0000
0.750 0.0253 0.01794 0.00969 -0.0067 0.9899 1.0000
1.000 0.0724 0.01859 0.01029 -0.0116 0.9826 1.0000
1.250 0.1121 0.01901 0.01070 -0.0149 0.9725 1.0000
1.500 0.1523 0.01945 0.01115 -0.0183 0.9628 1.0000
1.750 0.1975 0.01992 0.01166 -0.0225 0.9544 1.0000
2.000 0.2370 0.02026 0.01207 -0.0255 0.9439 1.0000
2.250 0.2743 0.02055 0.01244 -0.0280 0.9325 1.0000
2.500 0.3128 0.02081 0.01280 -0.0306 0.9213 1.0000
2.750 0.3534 0.02101 0.01312 -0.0335 0.9102 1.0000
3.000 0.4039 0.02106 0.01340 -0.0380 0.9014 1.0000
3.250 0.4432 0.02105 0.01358 -0.0403 0.8886 1.0000
3.500 0.4850 0.02090 0.01366 -0.0428 0.8756 1.0000
3.750 0.5300 0.02058 0.01366 -0.0456 0.8624 1.0000
4.000 0.5742 0.02010 0.01351 -0.0480 0.8490 1.0000
4.250 0.6493 0.01521 0.00897 -0.0480 0.7779 1.0000
4.500 0.6745 0.01427 0.00728 -0.0426 0.5549 1.0000
4.750 0.6546 0.01807 0.00821 -0.0338 0.1168 1.0000
5.000 0.6647 0.01980 0.00968 -0.0303 0.0814 1.0000
5.250 0.6779 0.02109 0.01098 -0.0275 0.0681 1.0000
5.500 0.6920 0.02260 0.01241 -0.0250 0.0605 1.0000
5.750 0.7146 0.02441 0.01423 -0.0235 0.0571 1.0000
6.000 0.7436 0.02636 0.01627 -0.0231 0.0542 1.0000
6.250 0.7703 0.02842 0.01835 -0.0228 0.0488 1.0000
6.500 0.8007 0.03147 0.02157 -0.0228 0.0479 1.0000
6.750 0.8270 0.03377 0.02438 -0.0213 0.0496 1.0000
7.000 0.8487 0.03725 0.02858 -0.0187 0.0543 1.0000
10.500 0.6112 0.10338 0.09890 0.0002 0.1624 1.0000
10.750 0.6036 0.10747 0.10296 -0.0008 0.1540 1.0000
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Polar data table (+)
Polar graphs
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