NACA 0010-34 a=0.8 c(li)=0.2 (naca001034a08cli02-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 0010-34 a=0.8 c(li)=0.2 (naca001034a08cli02-il) Reynolds number: 50,000 Max Cl/Cd: 30.79 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca001034a08cli02-il-50000-n5.txt Download as CSV file: xf-naca001034a08cli02-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4111 0.09209 0.08559 -0.0421 1.0000 0.0419
-9.250 -0.5166 0.09266 0.08584 -0.0426 1.0000 0.0420
-9.000 -0.5197 0.08840 0.08164 -0.0438 1.0000 0.0410
-8.750 -0.5282 0.08422 0.07752 -0.0452 1.0000 0.0402
-8.500 -0.5411 0.08068 0.07403 -0.0451 1.0000 0.0396
-8.250 -0.5536 0.07724 0.07061 -0.0442 1.0000 0.0389
-8.000 -0.5648 0.07377 0.06711 -0.0431 1.0000 0.0382
-7.750 -0.5745 0.07031 0.06359 -0.0416 1.0000 0.0375
-7.500 -0.5824 0.06684 0.06001 -0.0398 1.0000 0.0367
-7.250 -0.5882 0.06334 0.05635 -0.0377 1.0000 0.0359
-7.000 -0.5914 0.05982 0.05260 -0.0355 1.0000 0.0351
-6.750 -0.5919 0.05629 0.04878 -0.0332 1.0000 0.0343
-6.500 -0.5890 0.05283 0.04497 -0.0308 1.0000 0.0335
-6.250 -0.5830 0.04947 0.04119 -0.0284 1.0000 0.0329
-6.000 -0.5739 0.04629 0.03755 -0.0260 1.0000 0.0324
-5.750 -0.5622 0.04342 0.03429 -0.0240 1.0000 0.0327
-5.500 -0.5486 0.04089 0.03145 -0.0223 1.0000 0.0344
-5.250 -0.5325 0.03850 0.02866 -0.0206 1.0000 0.0363
-5.000 -0.5137 0.03613 0.02572 -0.0189 1.0000 0.0378
-4.750 -0.4924 0.03383 0.02299 -0.0174 1.0000 0.0385
-4.500 -0.4692 0.03175 0.02054 -0.0160 1.0000 0.0395
-4.250 -0.4449 0.02995 0.01841 -0.0147 1.0000 0.0410
-4.000 -0.4212 0.02846 0.01666 -0.0133 1.0000 0.0441
-3.750 -0.3999 0.02704 0.01517 -0.0122 1.0000 0.0514
-3.500 -0.3775 0.02593 0.01374 -0.0108 1.0000 0.0565
-3.250 -0.3551 0.02465 0.01235 -0.0100 1.0000 0.0645
-3.000 -0.3328 0.02344 0.01114 -0.0093 1.0000 0.0906
-2.750 -0.2494 0.02077 0.01211 -0.0123 1.0000 0.9596
-2.500 -0.1863 0.02076 0.01138 -0.0199 1.0000 0.9862
-2.250 -0.1484 0.02056 0.01076 -0.0233 1.0000 1.0000
-2.000 -0.1463 0.02031 0.01027 -0.0198 1.0000 1.0000
-1.750 -0.1417 0.02013 0.00989 -0.0166 1.0000 1.0000
-1.500 -0.1343 0.02003 0.00958 -0.0138 1.0000 1.0000
-1.250 -0.1248 0.01999 0.00933 -0.0114 1.0000 1.0000
-1.000 -0.1131 0.02001 0.00916 -0.0093 1.0000 1.0000
-0.750 -0.0995 0.02008 0.00904 -0.0075 1.0000 1.0000
-0.500 -0.0844 0.02021 0.00896 -0.0060 1.0000 1.0000
-0.250 -0.0642 0.02040 0.00900 -0.0055 0.9986 1.0000
0.000 -0.0278 0.02076 0.00919 -0.0082 0.9918 1.0000
0.250 0.0085 0.02113 0.00943 -0.0109 0.9848 1.0000
0.500 0.0453 0.02151 0.00969 -0.0136 0.9777 1.0000
0.750 0.0798 0.02184 0.00995 -0.0158 0.9692 1.0000
1.000 0.1140 0.02218 0.01026 -0.0180 0.9606 1.0000
1.250 0.1510 0.02255 0.01062 -0.0206 0.9527 1.0000
1.500 0.1850 0.02286 0.01095 -0.0226 0.9432 1.0000
1.750 0.2179 0.02316 0.01130 -0.0243 0.9331 1.0000
2.000 0.2525 0.02346 0.01170 -0.0263 0.9233 1.0000
2.250 0.2913 0.02375 0.01210 -0.0290 0.9145 1.0000
2.500 0.3222 0.02399 0.01247 -0.0300 0.9027 1.0000
2.750 0.3537 0.02422 0.01285 -0.0312 0.8908 1.0000
3.000 0.3859 0.02443 0.01330 -0.0324 0.8788 1.0000
3.250 0.4182 0.02461 0.01369 -0.0335 0.8662 1.0000
3.500 0.4508 0.02474 0.01407 -0.0345 0.8531 1.0000
3.750 0.4837 0.02481 0.01449 -0.0354 0.8393 1.0000
4.000 0.5171 0.02481 0.01482 -0.0363 0.8248 1.0000
4.250 0.5513 0.02470 0.01508 -0.0369 0.8095 1.0000
4.500 0.5832 0.02454 0.01533 -0.0370 0.7921 1.0000
4.750 0.6116 0.02439 0.01570 -0.0363 0.7715 1.0000
5.000 0.6515 0.02116 0.01255 -0.0308 0.6384 1.0000
5.250 0.6599 0.02246 0.01173 -0.0243 0.2867 1.0000
5.500 0.6587 0.02562 0.01341 -0.0205 0.1003 1.0000
5.750 0.6718 0.02755 0.01518 -0.0181 0.0731 1.0000
6.000 0.6872 0.02913 0.01682 -0.0162 0.0572 1.0000
6.250 0.7041 0.03099 0.01875 -0.0144 0.0512 1.0000
6.500 0.7299 0.03272 0.02082 -0.0133 0.0461 1.0000
6.750 0.7573 0.03515 0.02320 -0.0133 0.0389 1.0000
7.000 0.7903 0.03751 0.02614 -0.0131 0.0362 1.0000
7.250 0.8196 0.04047 0.02954 -0.0126 0.0348 1.0000
7.500 0.8422 0.04362 0.03317 -0.0114 0.0338 1.0000
7.750 0.8586 0.04669 0.03670 -0.0095 0.0325 1.0000
8.000 0.8702 0.04965 0.04007 -0.0074 0.0307 1.0000
8.250 0.8791 0.05261 0.04333 -0.0053 0.0291 1.0000
8.500 0.8847 0.05588 0.04690 -0.0031 0.0281 1.0000
8.750 0.8868 0.05939 0.05078 -0.0006 0.0279 1.0000
9.000 0.8852 0.06293 0.05469 0.0022 0.0280 1.0000
9.250 0.8788 0.06650 0.05861 0.0050 0.0282 1.0000
9.500 0.8675 0.07009 0.06251 0.0079 0.0285 1.0000
9.750 0.8512 0.07354 0.06621 0.0107 0.0288 1.0000
10.000 0.8331 0.07735 0.07022 0.0124 0.0292 1.0000
10.250 0.8138 0.08171 0.07474 0.0128 0.0295 1.0000
10.500 0.7943 0.08676 0.07992 0.0115 0.0299 1.0000
10.750 0.7756 0.09268 0.08594 0.0086 0.0304 1.0000
11.000 0.7589 0.09956 0.09286 0.0043 0.0309 1.0000
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Polar data table (+)
Polar graphs
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