NACA 0008-34 (naca000834-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 0008-34 (naca000834-il) Reynolds number: 50,000 Max Cl/Cd: 18.48 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca000834-il-50000-n5.txt Download as CSV file: xf-naca000834-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0008-34
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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.6438 0.09169 0.08504 -0.0167 1.0000 0.0415
-8.750 -0.6480 0.08705 0.08042 -0.0185 1.0000 0.0404
-8.500 -0.6555 0.08264 0.07601 -0.0199 1.0000 0.0392
-8.250 -0.6630 0.07824 0.07156 -0.0207 1.0000 0.0380
-8.000 -0.6797 0.07376 0.06657 -0.0219 1.0000 0.0339
-7.750 -0.6748 0.06936 0.06213 -0.0214 1.0000 0.0334
-7.500 -0.6726 0.06531 0.05791 -0.0207 1.0000 0.0331
-7.250 -0.6690 0.06138 0.05374 -0.0196 1.0000 0.0330
-7.000 -0.6636 0.05756 0.04963 -0.0184 1.0000 0.0328
-6.750 -0.6560 0.05386 0.04558 -0.0169 1.0000 0.0328
-6.500 -0.6461 0.05027 0.04153 -0.0152 1.0000 0.0326
-6.250 -0.6341 0.04680 0.03766 -0.0135 1.0000 0.0323
-6.000 -0.6199 0.04346 0.03389 -0.0117 1.0000 0.0319
-5.750 -0.6033 0.04031 0.03028 -0.0098 1.0000 0.0315
-5.500 -0.5843 0.03736 0.02687 -0.0081 1.0000 0.0314
-5.250 -0.5627 0.03461 0.02366 -0.0064 1.0000 0.0316
-5.000 -0.5390 0.03224 0.02080 -0.0049 1.0000 0.0329
-4.750 -0.5149 0.02986 0.01819 -0.0039 1.0000 0.0359
-4.500 -0.4893 0.02787 0.01602 -0.0028 1.0000 0.0390
-4.250 -0.4640 0.02616 0.01399 -0.0013 1.0000 0.0417
-4.000 -0.4427 0.02454 0.01223 0.0001 1.0000 0.0485
-3.750 -0.4217 0.02320 0.01064 0.0017 1.0000 0.0573
-3.500 -0.4014 0.02171 0.00911 0.0030 1.0000 0.0772
-3.250 -0.3253 0.01948 0.01042 0.0031 1.0000 0.9285
-3.000 -0.2734 0.01926 0.00949 -0.0018 1.0000 0.9484
-2.750 -0.2276 0.01896 0.00867 -0.0060 1.0000 0.9670
-2.500 -0.1790 0.01857 0.00780 -0.0109 1.0000 0.9820
-2.250 -0.1318 0.01815 0.00704 -0.0158 1.0000 0.9961
-2.000 -0.1065 0.01781 0.00652 -0.0164 1.0000 1.0000
-1.750 -0.0911 0.01756 0.00610 -0.0149 1.0000 1.0000
-1.500 -0.0764 0.01734 0.00579 -0.0132 1.0000 1.0000
-1.250 -0.0624 0.01716 0.00554 -0.0114 1.0000 1.0000
-1.000 -0.0491 0.01702 0.00535 -0.0093 1.0000 1.0000
-0.750 -0.0365 0.01691 0.00520 -0.0071 1.0000 1.0000
-0.500 -0.0241 0.01683 0.00508 -0.0048 1.0000 1.0000
-0.250 -0.0120 0.01679 0.00502 -0.0024 1.0000 1.0000
0.000 0.0000 0.01677 0.00500 0.0000 1.0000 1.0000
0.250 0.0120 0.01679 0.00502 0.0024 1.0000 1.0000
0.500 0.0241 0.01683 0.00508 0.0048 1.0000 1.0000
0.750 0.0365 0.01691 0.00520 0.0071 1.0000 1.0000
1.000 0.0491 0.01702 0.00534 0.0093 1.0000 1.0000
1.250 0.0624 0.01716 0.00554 0.0114 1.0000 1.0000
1.500 0.0764 0.01734 0.00579 0.0132 1.0000 1.0000
1.750 0.0912 0.01755 0.00610 0.0149 1.0000 1.0000
2.000 0.1066 0.01781 0.00652 0.0164 1.0000 1.0000
2.250 0.1317 0.01814 0.00704 0.0158 0.9962 1.0000
2.500 0.1789 0.01856 0.00779 0.0109 0.9821 1.0000
2.750 0.2275 0.01895 0.00867 0.0060 0.9671 1.0000
3.000 0.2734 0.01925 0.00948 0.0018 0.9485 1.0000
3.250 0.3252 0.01948 0.01041 -0.0031 0.9286 1.0000
3.500 0.4013 0.02171 0.00911 -0.0030 0.0773 1.0000
3.750 0.4216 0.02320 0.01064 -0.0016 0.0573 1.0000
4.000 0.4425 0.02453 0.01223 -0.0001 0.0485 1.0000
4.250 0.4639 0.02615 0.01398 0.0014 0.0417 1.0000
4.500 0.4891 0.02786 0.01601 0.0028 0.0390 1.0000
4.750 0.5147 0.02985 0.01818 0.0039 0.0360 1.0000
5.000 0.5388 0.03223 0.02079 0.0049 0.0329 1.0000
5.250 0.5626 0.03460 0.02365 0.0064 0.0316 1.0000
5.500 0.5842 0.03735 0.02685 0.0081 0.0314 1.0000
5.750 0.6033 0.04030 0.03027 0.0098 0.0315 1.0000
6.000 0.6198 0.04346 0.03389 0.0117 0.0319 1.0000
6.250 0.6341 0.04680 0.03765 0.0135 0.0323 1.0000
6.500 0.6462 0.05027 0.04153 0.0152 0.0326 1.0000
6.750 0.6561 0.05387 0.04559 0.0169 0.0328 1.0000
7.000 0.6637 0.05757 0.04964 0.0183 0.0329 1.0000
7.250 0.6693 0.06140 0.05376 0.0196 0.0330 1.0000
7.500 0.6728 0.06533 0.05794 0.0206 0.0332 1.0000
7.750 0.6751 0.06939 0.06216 0.0213 0.0334 1.0000
8.250 0.6633 0.07829 0.07161 0.0206 0.0380 1.0000
8.500 0.6560 0.08270 0.07607 0.0197 0.0393 1.0000
8.750 0.6487 0.08710 0.08048 0.0184 0.0404 1.0000
9.000 0.6444 0.09175 0.08510 0.0166 0.0416 1.0000
9.250 0.6392 0.09875 0.09210 0.0095 0.0484 1.0000
9.500 0.6374 0.10416 0.09744 0.0063 0.0519 1.0000
9.750 0.5153 0.09700 0.09053 0.0149 0.0491 1.0000
10.000 0.5114 0.10175 0.09523 0.0134 0.0518 1.0000
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Polar data table (+)
Polar graphs
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