NACA 0010-34 a=0.8 c(li)=0.2 (naca001034a08cli02-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 0010-34 a=0.8 c(li)=0.2 (naca001034a08cli02-il) Reynolds number: 50,000 Max Cl/Cd: 26.49 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca001034a08cli02-il-50000.txt Download as CSV file: xf-naca001034a08cli02-il-50000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4998 0.12648 0.11950 -0.0164 1.0000 0.2251
-10.250 -0.5164 0.12532 0.11846 -0.0181 1.0000 0.2346
-10.000 -0.5073 0.12126 0.11442 -0.0173 1.0000 0.2480
-9.750 -0.5008 0.11748 0.11058 -0.0167 1.0000 0.2614
-9.500 -0.4976 0.11409 0.10724 -0.0163 1.0000 0.2752
-9.250 -0.5000 0.11126 0.10448 -0.0159 1.0000 0.2897
-9.000 -0.4805 0.10660 0.09981 -0.0140 1.0000 0.3098
-8.750 -0.4830 0.10411 0.09739 -0.0130 1.0000 0.3299
-8.500 -0.3775 0.09138 0.08526 -0.0177 1.0000 0.3600
-8.250 -0.3772 0.08796 0.08190 -0.0163 1.0000 0.3739
-8.000 -0.3616 0.08334 0.07727 -0.0155 1.0000 0.3828
-7.750 -0.3640 0.07985 0.07384 -0.0142 1.0000 0.3926
-6.000 -0.5979 0.05674 0.04990 -0.0260 1.0000 0.1754
-5.750 -0.5871 0.05103 0.04332 -0.0259 1.0000 0.1356
-5.500 -0.5727 0.04691 0.03865 -0.0243 1.0000 0.1210
-5.250 -0.5566 0.04371 0.03458 -0.0221 1.0000 0.1100
-5.000 -0.5379 0.04017 0.03079 -0.0207 1.0000 0.1067
-4.750 -0.5166 0.03705 0.02709 -0.0190 1.0000 0.1009
-4.500 -0.4925 0.03490 0.02417 -0.0171 1.0000 0.0964
-4.250 -0.4671 0.03229 0.02123 -0.0160 1.0000 0.0954
-4.000 -0.4402 0.03017 0.01874 -0.0147 1.0000 0.0961
-3.750 -0.1416 0.02356 0.01482 -0.0434 1.0000 1.0000
-3.500 -0.1426 0.02285 0.01391 -0.0407 1.0000 1.0000
-3.250 -0.1442 0.02224 0.01312 -0.0377 1.0000 1.0000
-3.000 -0.1459 0.02172 0.01242 -0.0343 1.0000 1.0000
-2.750 -0.1475 0.02127 0.01180 -0.0307 1.0000 1.0000
-2.500 -0.1485 0.02088 0.01125 -0.0270 1.0000 1.0000
-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 -0.0682 0.02038 0.00898 -0.0047 1.0000 1.0000
0.000 -0.0512 0.02059 0.00905 -0.0036 1.0000 1.0000
0.250 -0.0336 0.02084 0.00919 -0.0026 1.0000 1.0000
0.500 -0.0155 0.02113 0.00938 -0.0018 1.0000 1.0000
0.750 0.0028 0.02146 0.00960 -0.0010 1.0000 1.0000
1.000 0.0213 0.02182 0.00991 -0.0004 1.0000 1.0000
1.250 0.0398 0.02223 0.01027 0.0002 1.0000 1.0000
1.500 0.0584 0.02268 0.01070 0.0007 1.0000 1.0000
1.750 0.0770 0.02318 0.01119 0.0012 1.0000 1.0000
2.000 0.0954 0.02372 0.01174 0.0015 1.0000 1.0000
2.250 0.1137 0.02431 0.01235 0.0018 1.0000 1.0000
2.500 0.1317 0.02496 0.01304 0.0021 1.0000 1.0000
2.750 0.1495 0.02567 0.01380 0.0023 1.0000 1.0000
3.000 0.1669 0.02644 0.01467 0.0024 1.0000 1.0000
3.250 0.1840 0.02728 0.01559 0.0024 1.0000 1.0000
3.500 0.2006 0.02819 0.01661 0.0024 1.0000 1.0000
3.750 0.2372 0.02957 0.01816 -0.0016 0.9911 1.0000
4.000 0.2940 0.03126 0.02019 -0.0094 0.9702 1.0000
4.250 0.3444 0.03268 0.02192 -0.0155 0.9478 1.0000
4.500 0.3958 0.03395 0.02357 -0.0213 0.9246 1.0000
4.750 0.4483 0.03499 0.02511 -0.0268 0.9002 1.0000
5.000 0.4983 0.03570 0.02632 -0.0312 0.8740 1.0000
5.250 0.5416 0.03612 0.02729 -0.0339 0.8458 1.0000
5.500 0.6659 0.02514 0.01410 -0.0192 0.1829 1.0000
5.750 0.6775 0.02770 0.01612 -0.0163 0.1333 1.0000
6.000 0.7096 0.03013 0.01849 -0.0159 0.1098 1.0000
6.250 0.7590 0.03324 0.02165 -0.0178 0.0967 1.0000
6.500 0.7937 0.03638 0.02495 -0.0181 0.0875 1.0000
6.750 0.8241 0.03966 0.02870 -0.0173 0.0868 1.0000
7.000 0.8489 0.04328 0.03290 -0.0159 0.0879 1.0000
7.250 0.8707 0.04747 0.03741 -0.0145 0.0899 1.0000
7.500 0.8836 0.05045 0.04112 -0.0114 0.0928 1.0000
7.750 0.8891 0.05424 0.04565 -0.0079 0.0976 1.0000
8.000 0.8958 0.05850 0.05030 -0.0054 0.1009 1.0000
8.250 0.8999 0.06262 0.05491 -0.0027 0.1072 1.0000
8.500 0.8982 0.06779 0.06045 -0.0004 0.1156 1.0000
8.750 0.8983 0.07350 0.06658 0.0012 0.1322 1.0000
9.000 0.7763 0.06464 0.05839 0.0132 0.1262 1.0000
9.250 0.7577 0.06945 0.06332 0.0151 0.1338 1.0000
9.500 0.7160 0.07424 0.06820 0.0160 0.1359 1.0000
9.750 0.6814 0.08019 0.07405 0.0145 0.1379 1.0000
10.000 0.6600 0.08726 0.08114 0.0116 0.1472 1.0000
10.250 0.6229 0.09556 0.08935 0.0059 0.1508 1.0000
10.500 0.5948 0.10456 0.09828 0.0000 0.1776 1.0000
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Polar data table (+)
Polar graphs
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