NACA 0010-66 (naca001066-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 0010-66 (naca001066-il) Reynolds number: 200,000 Max Cl/Cd: 34.4 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca001066-il-200000-n5.txt Download as CSV file: xf-naca001066-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0010-66
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.8772 0.06435 0.06055 -0.0444 1.0000 0.0182
-11.500 -0.9193 0.05911 0.05511 -0.0398 1.0000 0.0179
-11.250 -0.9572 0.05514 0.05091 -0.0330 1.0000 0.0179
-11.000 -0.9914 0.05209 0.04763 -0.0249 1.0000 0.0179
-10.750 -1.0213 0.04948 0.04478 -0.0164 1.0000 0.0181
-10.500 -1.0439 0.04614 0.04109 -0.0091 1.0000 0.0185
-10.250 -1.0610 0.04275 0.03727 -0.0023 1.0000 0.0190
-10.000 -1.0713 0.03958 0.03359 0.0038 1.0000 0.0197
-9.750 -1.0714 0.03700 0.03057 0.0083 0.9996 0.0204
-9.500 -1.0568 0.03568 0.02914 0.0099 0.9983 0.0211
-9.250 -1.0398 0.03488 0.02825 0.0112 0.9971 0.0219
-9.000 -1.0229 0.03397 0.02714 0.0127 0.9961 0.0231
-8.750 -1.0064 0.03263 0.02549 0.0143 0.9951 0.0247
-8.500 -0.9891 0.03118 0.02366 0.0160 0.9943 0.0262
-8.250 -0.9724 0.02969 0.02185 0.0179 0.9934 0.0274
-8.000 -0.9543 0.02869 0.02079 0.0193 0.9924 0.0288
-7.750 -0.9337 0.02806 0.02008 0.0203 0.9912 0.0304
-7.500 -0.9119 0.02724 0.01906 0.0212 0.9901 0.0321
-7.250 -0.8896 0.02639 0.01799 0.0220 0.9892 0.0338
-7.000 -0.8667 0.02580 0.01717 0.0229 0.9884 0.0352
-6.750 -0.8441 0.02454 0.01583 0.0235 0.9879 0.0371
-6.500 -0.8208 0.02387 0.01511 0.0241 0.9872 0.0387
-6.250 -0.7969 0.02334 0.01451 0.0246 0.9866 0.0406
-6.000 -0.7725 0.02276 0.01381 0.0251 0.9860 0.0423
-5.750 -0.7476 0.02217 0.01312 0.0255 0.9855 0.0437
-5.500 -0.7255 0.02165 0.01249 0.0265 0.9843 0.0449
-5.250 -0.7037 0.02102 0.01182 0.0276 0.9831 0.0467
-5.000 -0.6822 0.02046 0.01124 0.0287 0.9821 0.0488
-4.750 -0.6599 0.02004 0.01078 0.0296 0.9811 0.0506
-4.500 -0.6372 0.01966 0.01036 0.0305 0.9802 0.0527
-4.250 -0.6140 0.01934 0.00997 0.0313 0.9793 0.0552
-4.000 -0.5902 0.01903 0.00961 0.0320 0.9784 0.0581
-3.750 -0.5655 0.01870 0.00931 0.0325 0.9775 0.0637
-3.500 -0.5400 0.01843 0.00907 0.0327 0.9766 0.0735
-3.250 -0.5152 0.01815 0.00888 0.0331 0.9759 0.0905
-3.000 -0.4903 0.01792 0.00872 0.0335 0.9753 0.1132
-2.750 -0.4711 0.01761 0.00852 0.0351 0.9740 0.1378
-2.500 -0.4507 0.01732 0.00837 0.0364 0.9727 0.1694
-2.250 -0.4294 0.01699 0.00824 0.0375 0.9711 0.2144
-2.000 -0.4083 0.01663 0.00813 0.0386 0.9698 0.2752
-1.750 -0.3070 0.01637 0.01057 0.0236 0.9789 0.8921
-1.500 -0.2810 0.01697 0.01111 0.0245 0.9783 0.9173
-1.250 -0.2466 0.01750 0.01156 0.0232 0.9781 0.9301
-1.000 -0.2131 0.01794 0.01195 0.0221 0.9778 0.9403
-0.750 -0.1774 0.01844 0.01240 0.0205 0.9778 0.9507
-0.500 -0.1067 0.01947 0.01340 0.0115 0.9817 0.9665
-0.250 -0.0488 0.02000 0.01392 0.0048 0.9843 0.9773
0.000 0.0000 0.02013 0.01405 0.0000 0.9832 0.9832
0.250 0.0486 0.02000 0.01392 -0.0048 0.9773 0.9844
0.500 0.1069 0.01946 0.01340 -0.0115 0.9664 0.9816
0.750 0.1775 0.01844 0.01240 -0.0205 0.9507 0.9778
1.000 0.2132 0.01794 0.01194 -0.0221 0.9403 0.9778
1.250 0.2466 0.01749 0.01156 -0.0233 0.9301 0.9781
1.500 0.2810 0.01696 0.01110 -0.0245 0.9172 0.9783
1.750 0.3067 0.01637 0.01057 -0.0235 0.8917 0.9790
2.000 0.4082 0.01663 0.00813 -0.0386 0.2749 0.9698
2.250 0.4294 0.01699 0.00823 -0.0375 0.2140 0.9712
2.500 0.4506 0.01732 0.00837 -0.0364 0.1692 0.9727
2.750 0.4710 0.01761 0.00852 -0.0351 0.1377 0.9740
3.000 0.4902 0.01791 0.00871 -0.0335 0.1132 0.9753
3.250 0.5152 0.01815 0.00888 -0.0331 0.0904 0.9759
3.500 0.5400 0.01843 0.00907 -0.0327 0.0734 0.9766
3.750 0.5655 0.01869 0.00931 -0.0325 0.0638 0.9775
4.000 0.5902 0.01902 0.00960 -0.0320 0.0581 0.9785
4.250 0.6139 0.01933 0.00997 -0.0313 0.0552 0.9793
4.500 0.6371 0.01966 0.01035 -0.0305 0.0527 0.9802
4.750 0.6599 0.02003 0.01077 -0.0296 0.0506 0.9812
5.000 0.6821 0.02046 0.01123 -0.0287 0.0488 0.9821
5.250 0.7036 0.02101 0.01181 -0.0276 0.0467 0.9831
5.500 0.7254 0.02165 0.01249 -0.0265 0.0449 0.9843
5.750 0.7476 0.02217 0.01311 -0.0255 0.0437 0.9855
6.000 0.7725 0.02276 0.01380 -0.0251 0.0423 0.9860
6.250 0.7970 0.02333 0.01450 -0.0246 0.0406 0.9866
6.500 0.8208 0.02386 0.01510 -0.0241 0.0386 0.9872
6.750 0.8441 0.02454 0.01583 -0.0235 0.0371 0.9879
7.000 0.8668 0.02580 0.01717 -0.0229 0.0353 0.9884
7.250 0.8897 0.02639 0.01798 -0.0221 0.0338 0.9892
7.500 0.9121 0.02723 0.01905 -0.0212 0.0321 0.9901
7.750 0.9339 0.02805 0.02007 -0.0203 0.0304 0.9912
8.000 0.9544 0.02867 0.02077 -0.0193 0.0288 0.9925
8.250 0.9725 0.02967 0.02183 -0.0179 0.0274 0.9934
8.500 0.9891 0.03117 0.02365 -0.0161 0.0262 0.9943
8.750 1.0065 0.03264 0.02550 -0.0144 0.0247 0.9951
9.000 1.0230 0.03397 0.02714 -0.0127 0.0231 0.9961
9.250 1.0400 0.03486 0.02822 -0.0112 0.0219 0.9972
9.500 1.0569 0.03569 0.02915 -0.0099 0.0211 0.9984
9.750 1.0716 0.03698 0.03056 -0.0083 0.0204 0.9997
10.000 1.0714 0.03956 0.03357 -0.0039 0.0197 1.0000
10.250 1.0610 0.04275 0.03726 0.0023 0.0190 1.0000
10.500 1.0441 0.04613 0.04107 0.0091 0.0185 1.0000
10.750 1.0218 0.04944 0.04474 0.0164 0.0180 1.0000
11.000 0.9915 0.05210 0.04765 0.0249 0.0179 1.0000
11.250 0.9576 0.05513 0.05090 0.0329 0.0178 1.0000
11.500 0.9198 0.05909 0.05508 0.0397 0.0179 1.0000
11.750 0.8769 0.06441 0.06061 0.0444 0.0182 1.0000
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Polar data table (+)
Polar graphs
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