NACA 0010-34 a=0.8 c(li)=0.2 (naca001034a08cli02-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 0010-34 a=0.8 c(li)=0.2 (naca001034a08cli02-il) Reynolds number: 1,000,000 Max Cl/Cd: 78.67 at α=2° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca001034a08cli02-il-1000000-n5.txt Download as CSV file: xf-naca001034a08cli02-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5285 0.08041 0.07886 -0.0403 1.0000 0.0014
-9.250 -0.5383 0.07437 0.07286 -0.0447 1.0000 0.0013
-9.000 -0.5513 0.06632 0.06477 -0.0542 0.9968 0.0013
-8.750 -0.5565 0.05926 0.05757 -0.0598 0.9905 0.0013
-8.500 -0.5571 0.05243 0.05055 -0.0632 0.9853 0.0013
-8.250 -0.5572 0.04604 0.04391 -0.0640 0.9785 0.0013
-8.000 -0.5569 0.03940 0.03694 -0.0631 0.9713 0.0012
-7.750 -0.5592 0.03111 0.02811 -0.0602 0.9639 0.0013
-7.500 -0.5621 0.02196 0.01816 -0.0553 0.9558 0.0015
-7.250 -0.5449 0.01890 0.01471 -0.0536 0.9516 0.0017
-7.000 -0.5231 0.01756 0.01317 -0.0528 0.9471 0.0018
-6.750 -0.4997 0.01662 0.01208 -0.0522 0.9432 0.0019
-6.500 -0.4796 0.01444 0.00955 -0.0509 0.9396 0.0021
-6.250 -0.4587 0.01288 0.00771 -0.0497 0.9353 0.0022
-6.000 -0.4360 0.01191 0.00659 -0.0489 0.9312 0.0024
-5.750 -0.4121 0.01121 0.00578 -0.0483 0.9277 0.0026
-5.500 -0.3866 0.01085 0.00538 -0.0480 0.9240 0.0030
-5.250 -0.3605 0.01059 0.00510 -0.0479 0.9202 0.0035
-5.000 -0.3348 0.01023 0.00469 -0.0477 0.9165 0.0041
-4.750 -0.3098 0.00973 0.00410 -0.0472 0.9131 0.0048
-4.500 -0.2831 0.00954 0.00388 -0.0472 0.9091 0.0055
-4.250 -0.2583 0.00901 0.00324 -0.0467 0.9049 0.0067
-4.000 -0.2322 0.00867 0.00279 -0.0465 0.9012 0.0077
-3.750 -0.2054 0.00847 0.00258 -0.0465 0.8972 0.0096
-3.500 -0.1786 0.00826 0.00233 -0.0464 0.8926 0.0114
-3.250 -0.1514 0.00814 0.00218 -0.0464 0.8884 0.0122
-3.000 -0.1244 0.00795 0.00194 -0.0464 0.8837 0.0133
-2.750 -0.0973 0.00779 0.00170 -0.0463 0.8784 0.0151
-2.500 -0.0702 0.00764 0.00154 -0.0463 0.8734 0.0215
-2.250 -0.0447 0.00723 0.00135 -0.0460 0.8672 0.0915
-2.000 -0.0221 0.00649 0.00113 -0.0455 0.8609 0.2564
-1.750 0.0007 0.00581 0.00099 -0.0450 0.8535 0.4154
-1.500 0.0248 0.00538 0.00089 -0.0445 0.8464 0.5224
-1.250 0.0484 0.00497 0.00084 -0.0439 0.8386 0.6334
-1.000 0.0741 0.00479 0.00082 -0.0435 0.8311 0.6890
-0.750 0.1012 0.00475 0.00077 -0.0435 0.8230 0.7099
-0.500 0.1281 0.00469 0.00076 -0.0434 0.8141 0.7348
-0.250 0.1550 0.00465 0.00075 -0.0433 0.8047 0.7556
0.000 0.1820 0.00463 0.00074 -0.0432 0.7943 0.7721
0.250 0.2090 0.00463 0.00074 -0.0431 0.7825 0.7869
0.500 0.2359 0.00463 0.00074 -0.0430 0.7697 0.8009
0.750 0.2626 0.00465 0.00076 -0.0428 0.7554 0.8148
1.000 0.2889 0.00468 0.00079 -0.0426 0.7382 0.8295
1.250 0.3146 0.00474 0.00083 -0.0422 0.7160 0.8453
1.500 0.3402 0.00480 0.00090 -0.0418 0.6936 0.8623
1.750 0.3657 0.00488 0.00097 -0.0414 0.6736 0.8811
2.000 0.3910 0.00497 0.00106 -0.0409 0.6494 0.9009
2.250 0.4109 0.00544 0.00121 -0.0393 0.5610 0.9216
2.500 0.4317 0.00597 0.00141 -0.0381 0.4698 0.9395
2.750 0.4551 0.00646 0.00162 -0.0374 0.3930 0.9530
3.000 0.4745 0.00744 0.00198 -0.0363 0.2408 0.9645
3.250 0.4982 0.00833 0.00235 -0.0361 0.1118 0.9721
3.500 0.5245 0.00893 0.00266 -0.0363 0.0397 0.9783
3.750 0.5540 0.00926 0.00290 -0.0369 0.0183 0.9830
4.000 0.5839 0.00950 0.00313 -0.0377 0.0148 0.9869
4.250 0.6162 0.00976 0.00343 -0.0389 0.0127 0.9891
4.500 0.6473 0.01005 0.00378 -0.0399 0.0119 0.9917
4.750 0.6767 0.01043 0.00428 -0.0406 0.0110 0.9944
5.000 0.7079 0.01074 0.00463 -0.0417 0.0100 0.9960
5.250 0.7402 0.01082 0.00467 -0.0431 0.0087 0.9976
5.500 0.7714 0.01103 0.00483 -0.0444 0.0058 0.9993
5.750 0.7963 0.01135 0.00515 -0.0441 0.0040 1.0000
6.000 0.8165 0.01166 0.00547 -0.0428 0.0031 1.0000
6.250 0.8362 0.01203 0.00584 -0.0413 0.0023 1.0000
6.500 0.8548 0.01253 0.00642 -0.0396 0.0018 1.0000
6.750 0.8714 0.01325 0.00726 -0.0374 0.0015 1.0000
7.000 0.8910 0.01369 0.00779 -0.0360 0.0015 1.0000
7.250 0.9110 0.01413 0.00829 -0.0347 0.0014 1.0000
7.500 0.9308 0.01465 0.00888 -0.0334 0.0012 1.0000
7.750 0.9499 0.01529 0.00961 -0.0320 0.0011 1.0000
8.000 0.9681 0.01609 0.01052 -0.0304 0.0010 1.0000
8.250 0.9855 0.01707 0.01164 -0.0287 0.0009 1.0000
8.500 1.0023 0.01825 0.01299 -0.0269 0.0008 1.0000
8.750 1.0183 0.01971 0.01465 -0.0250 0.0008 1.0000
9.000 1.0330 0.02162 0.01682 -0.0229 0.0008 1.0000
9.250 1.0442 0.02445 0.02003 -0.0203 0.0007 1.0000
9.500 1.0232 0.03451 0.03109 -0.0123 0.0008 1.0000
9.750 0.9924 0.04420 0.04141 -0.0042 0.0008 1.0000
10.000 0.9707 0.04998 0.04751 0.0014 0.0008 1.0000
10.250 0.9483 0.05423 0.05197 0.0064 0.0009 1.0000
10.500 0.9260 0.05844 0.05635 0.0099 0.0009 1.0000
10.750 0.9038 0.06289 0.06095 0.0118 0.0009 1.0000
11.000 0.8809 0.06796 0.06616 0.0119 0.0009 1.0000
11.250 0.8588 0.07379 0.07211 0.0100 0.0009 1.0000
11.500 0.8368 0.08109 0.07952 0.0055 0.0009 1.0000
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Polar data table (+)
Polar graphs
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