NACA 0010 (naca0010-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 0010 (naca0010-il) Reynolds number: 50,000 Max Cl/Cd: 25.72 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca0010-il-50000-n5.txt Download as CSV file: xf-naca0010-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0010
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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.8297 0.07541 0.06782 -0.0232 1.0000 0.0595
-10.500 -0.8517 0.07046 0.06270 -0.0240 1.0000 0.0595
-10.250 -0.8713 0.06587 0.05785 -0.0235 1.0000 0.0596
-10.000 -0.8721 0.06242 0.05434 -0.0228 1.0000 0.0608
-9.750 -0.8666 0.05990 0.05175 -0.0220 1.0000 0.0629
-9.500 -0.8659 0.05668 0.04829 -0.0211 1.0000 0.0649
-9.250 -0.8657 0.05301 0.04425 -0.0199 1.0000 0.0668
-9.000 -0.8623 0.04925 0.04002 -0.0186 1.0000 0.0684
-8.750 -0.8549 0.04575 0.03595 -0.0172 1.0000 0.0704
-8.500 -0.8423 0.04300 0.03286 -0.0160 1.0000 0.0735
-8.250 -0.8250 0.04102 0.03076 -0.0151 1.0000 0.0771
-8.000 -0.8070 0.03866 0.02807 -0.0141 1.0000 0.0801
-7.750 -0.7872 0.03639 0.02534 -0.0131 1.0000 0.0834
-7.500 -0.7667 0.03458 0.02341 -0.0123 1.0000 0.0881
-7.250 -0.7454 0.03305 0.02176 -0.0114 1.0000 0.0935
-7.000 -0.7219 0.03138 0.01975 -0.0105 1.0000 0.0985
-6.750 -0.6997 0.02989 0.01831 -0.0096 1.0000 0.1037
-6.500 -0.6771 0.02859 0.01681 -0.0087 1.0000 0.1120
-6.250 -0.6563 0.02738 0.01565 -0.0077 1.0000 0.1232
-6.000 -0.6352 0.02617 0.01445 -0.0066 1.0000 0.1372
-5.750 -0.6141 0.02497 0.01327 -0.0056 1.0000 0.1563
-5.500 -0.5940 0.02382 0.01224 -0.0046 1.0000 0.1856
-5.250 -0.5744 0.02272 0.01140 -0.0035 1.0000 0.2264
-5.000 -0.5553 0.02172 0.01071 -0.0023 1.0000 0.2809
-4.750 -0.5365 0.02086 0.01016 -0.0009 1.0000 0.3432
-4.500 -0.5174 0.02016 0.00969 0.0007 1.0000 0.4043
-4.250 -0.4984 0.01959 0.00932 0.0026 1.0000 0.4613
-4.000 -0.4792 0.01912 0.00903 0.0045 1.0000 0.5163
-3.750 -0.4595 0.01872 0.00881 0.0066 1.0000 0.5689
-3.500 -0.4392 0.01840 0.00862 0.0088 1.0000 0.6193
-3.250 -0.4182 0.01816 0.00849 0.0109 1.0000 0.6669
-3.000 -0.3959 0.01799 0.00840 0.0130 1.0000 0.7117
-2.750 -0.3721 0.01790 0.00833 0.0147 1.0000 0.7542
-2.500 -0.3464 0.01786 0.00828 0.0161 1.0000 0.7953
-2.250 -0.3153 0.01789 0.00828 0.0164 1.0000 0.8324
-2.000 -0.2812 0.01794 0.00824 0.0159 1.0000 0.8677
-1.750 -0.2421 0.01800 0.00819 0.0142 1.0000 0.8996
-1.500 -0.1958 0.01804 0.00810 0.0108 1.0000 0.9266
-1.250 -0.1450 0.01803 0.00797 0.0062 1.0000 0.9505
-1.000 -0.0925 0.01794 0.00777 0.0009 1.0000 0.9724
-0.750 -0.0386 0.01776 0.00752 -0.0049 1.0000 0.9917
-0.500 -0.0110 0.01757 0.00732 -0.0060 1.0000 1.0000
-0.250 -0.0053 0.01745 0.00721 -0.0031 1.0000 1.0000
0.000 0.0000 0.01742 0.00718 0.0000 1.0000 1.0000
0.250 0.0053 0.01745 0.00721 0.0031 1.0000 1.0000
0.500 0.0110 0.01757 0.00731 0.0060 1.0000 1.0000
0.750 0.0386 0.01776 0.00752 0.0049 0.9917 1.0000
1.000 0.0925 0.01794 0.00777 -0.0009 0.9724 1.0000
1.250 0.1450 0.01803 0.00796 -0.0062 0.9505 1.0000
1.500 0.1958 0.01804 0.00810 -0.0108 0.9266 1.0000
1.750 0.2420 0.01800 0.00819 -0.0142 0.8996 1.0000
2.000 0.2811 0.01794 0.00824 -0.0159 0.8677 1.0000
2.250 0.3153 0.01789 0.00828 -0.0164 0.8324 1.0000
2.500 0.3463 0.01786 0.00828 -0.0161 0.7953 1.0000
2.750 0.3720 0.01790 0.00833 -0.0147 0.7542 1.0000
3.000 0.3959 0.01799 0.00840 -0.0130 0.7117 1.0000
3.250 0.4181 0.01816 0.00849 -0.0109 0.6669 1.0000
3.500 0.4392 0.01840 0.00862 -0.0088 0.6193 1.0000
3.750 0.4594 0.01872 0.00881 -0.0066 0.5689 1.0000
4.000 0.4791 0.01912 0.00903 -0.0045 0.5163 1.0000
4.250 0.4984 0.01959 0.00932 -0.0025 0.4614 1.0000
4.500 0.5173 0.02016 0.00969 -0.0007 0.4043 1.0000
4.750 0.5365 0.02086 0.01016 0.0009 0.3432 1.0000
5.000 0.5553 0.02172 0.01071 0.0023 0.2809 1.0000
5.250 0.5744 0.02271 0.01140 0.0035 0.2264 1.0000
5.500 0.5940 0.02382 0.01224 0.0046 0.1856 1.0000
5.750 0.6141 0.02497 0.01327 0.0056 0.1563 1.0000
6.000 0.6352 0.02617 0.01445 0.0066 0.1372 1.0000
6.250 0.6563 0.02738 0.01565 0.0077 0.1232 1.0000
6.500 0.6772 0.02859 0.01681 0.0087 0.1120 1.0000
6.750 0.6998 0.02989 0.01831 0.0096 0.1037 1.0000
7.000 0.7219 0.03138 0.01975 0.0105 0.0985 1.0000
7.250 0.7454 0.03305 0.02175 0.0114 0.0935 1.0000
7.500 0.7667 0.03458 0.02340 0.0123 0.0880 1.0000
7.750 0.7872 0.03638 0.02534 0.0131 0.0834 1.0000
8.000 0.8071 0.03866 0.02807 0.0141 0.0801 1.0000
8.250 0.8251 0.04102 0.03076 0.0151 0.0771 1.0000
8.500 0.8424 0.04300 0.03286 0.0160 0.0735 1.0000
8.750 0.8550 0.04575 0.03596 0.0172 0.0704 1.0000
9.000 0.8624 0.04926 0.04002 0.0186 0.0684 1.0000
9.250 0.8659 0.05301 0.04425 0.0199 0.0668 1.0000
9.500 0.8661 0.05668 0.04830 0.0210 0.0649 1.0000
9.750 0.8669 0.05990 0.05175 0.0220 0.0629 1.0000
10.000 0.8725 0.06241 0.05432 0.0228 0.0608 1.0000
10.250 0.8714 0.06590 0.05788 0.0234 0.0596 1.0000
10.500 0.8519 0.07050 0.06274 0.0239 0.0595 1.0000
10.750 0.8299 0.07546 0.06787 0.0231 0.0595 1.0000
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Polar data table (+)
Polar graphs
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