NACA 0010-35 (naca001035-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 0010-35 (naca001035-il) Reynolds number: 100,000 Max Cl/Cd: 23.95 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca001035-il-100000.txt Download as CSV file: xf-naca001035-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0010-35
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.6347 0.09518 0.09030 -0.0385 1.0000 0.0946
-9.500 -0.6604 0.09188 0.08700 -0.0382 1.0000 0.0948
-9.250 -0.6878 0.08966 0.08477 -0.0349 1.0000 0.0950
-9.000 -0.6688 0.08393 0.07913 -0.0345 1.0000 0.0995
-8.750 -0.6818 0.08130 0.07653 -0.0313 1.0000 0.1019
-8.500 -0.6999 0.07860 0.07380 -0.0280 1.0000 0.1042
-8.250 -0.7245 0.07639 0.07147 -0.0239 1.0000 0.1071
-8.000 -0.7622 0.07642 0.07111 -0.0173 1.0000 0.1089
-7.750 -0.7387 0.06975 0.06478 -0.0176 1.0000 0.1149
-7.500 -0.7647 0.06935 0.06397 -0.0116 1.0000 0.1220
-5.000 -0.6841 0.03475 0.02576 0.0222 1.0000 0.0678
-4.750 -0.6610 0.03108 0.02178 0.0237 1.0000 0.0620
-4.500 -0.6356 0.02893 0.01894 0.0260 1.0000 0.0572
-4.250 -0.6089 0.02694 0.01666 0.0270 1.0000 0.0569
-4.000 -0.5831 0.02504 0.01477 0.0273 1.0000 0.0631
-3.750 -0.5557 0.02355 0.01312 0.0281 1.0000 0.0662
-3.500 -0.5307 0.02217 0.01166 0.0291 1.0000 0.0696
-3.250 -0.1356 0.02121 0.01333 -0.0324 1.0000 1.0000
-3.000 -0.1246 0.02085 0.01286 -0.0303 1.0000 1.0000
-2.750 -0.1137 0.02055 0.01245 -0.0281 1.0000 1.0000
-2.500 -0.1028 0.02028 0.01209 -0.0259 1.0000 1.0000
-2.250 -0.0921 0.02004 0.01174 -0.0235 1.0000 1.0000
-2.000 -0.0816 0.01984 0.01147 -0.0211 1.0000 1.0000
-1.750 -0.0711 0.01967 0.01124 -0.0186 1.0000 1.0000
-1.500 -0.0608 0.01952 0.01104 -0.0160 1.0000 1.0000
-1.250 -0.0505 0.01940 0.01088 -0.0134 1.0000 1.0000
-1.000 -0.0403 0.01930 0.01074 -0.0108 1.0000 1.0000
-0.750 -0.0302 0.01923 0.01063 -0.0081 1.0000 1.0000
-0.500 -0.0201 0.01917 0.01056 -0.0054 1.0000 1.0000
-0.250 -0.0100 0.01914 0.01052 -0.0027 1.0000 1.0000
0.000 0.0000 0.01913 0.01050 0.0000 1.0000 1.0000
0.250 0.0100 0.01914 0.01051 0.0027 1.0000 1.0000
0.500 0.0201 0.01917 0.01056 0.0054 1.0000 1.0000
0.750 0.0302 0.01923 0.01063 0.0081 1.0000 1.0000
1.000 0.0403 0.01930 0.01074 0.0108 1.0000 1.0000
1.250 0.0505 0.01940 0.01087 0.0134 1.0000 1.0000
1.500 0.0607 0.01952 0.01103 0.0160 1.0000 1.0000
1.750 0.0711 0.01966 0.01123 0.0186 1.0000 1.0000
2.000 0.0816 0.01983 0.01146 0.0211 1.0000 1.0000
2.250 0.0921 0.02003 0.01173 0.0235 1.0000 1.0000
2.500 0.1028 0.02027 0.01208 0.0259 1.0000 1.0000
2.750 0.1137 0.02053 0.01244 0.0281 1.0000 1.0000
3.000 0.1246 0.02084 0.01284 0.0303 1.0000 1.0000
3.250 0.1356 0.02119 0.01331 0.0324 1.0000 1.0000
3.500 0.5306 0.02215 0.01164 -0.0291 0.0696 1.0000
3.750 0.5557 0.02355 0.01311 -0.0280 0.0662 1.0000
4.000 0.5830 0.02504 0.01476 -0.0273 0.0631 1.0000
4.250 0.6089 0.02693 0.01665 -0.0270 0.0569 1.0000
4.500 0.6356 0.02893 0.01894 -0.0260 0.0572 1.0000
4.750 0.6610 0.03108 0.02177 -0.0237 0.0620 1.0000
5.000 0.6841 0.03474 0.02575 -0.0222 0.0678 1.0000
7.250 0.7537 0.06406 0.05889 0.0103 0.1279 1.0000
7.500 0.7647 0.06935 0.06397 0.0116 0.1220 1.0000
7.750 0.7387 0.06974 0.06477 0.0176 0.1149 1.0000
8.000 0.7622 0.07640 0.07109 0.0173 0.1089 1.0000
8.250 0.7245 0.07637 0.07146 0.0239 0.1071 1.0000
8.500 0.7000 0.07860 0.07380 0.0280 0.1042 1.0000
8.750 0.6820 0.08130 0.07652 0.0313 0.1018 1.0000
9.000 0.7161 0.08775 0.08279 0.0309 0.0953 1.0000
9.250 0.6878 0.08965 0.08476 0.0349 0.0950 1.0000
9.500 0.6603 0.09187 0.08699 0.0382 0.0948 1.0000
9.750 0.6346 0.09520 0.09032 0.0384 0.0945 1.0000
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Polar data table (+)
Polar graphs
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