NACA 0010-34 a=0.8 c(li)=0.2 (naca001034a08cli02-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 0010-34 a=0.8 c(li)=0.2 (naca001034a08cli02-il) Reynolds number: 100,000 Max Cl/Cd: 46.01 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca001034a08cli02-il-100000-n5.txt Download as CSV file: xf-naca001034a08cli02-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3938 0.09266 0.08799 -0.0392 1.0000 0.0249
-9.750 -0.3995 0.08817 0.08354 -0.0402 1.0000 0.0240
-9.500 -0.5014 0.09468 0.08977 -0.0370 1.0000 0.0264
-9.250 -0.5050 0.09009 0.08524 -0.0388 1.0000 0.0249
-9.000 -0.5111 0.08510 0.08031 -0.0415 1.0000 0.0238
-8.750 -0.5218 0.07965 0.07493 -0.0452 1.0000 0.0230
-8.500 -0.5388 0.07548 0.07079 -0.0462 1.0000 0.0226
-8.250 -0.5578 0.07206 0.06737 -0.0446 1.0000 0.0220
-8.000 -0.5750 0.06809 0.06333 -0.0429 1.0000 0.0211
-7.500 -0.5864 0.06215 0.05692 -0.0375 1.0000 0.0181
-7.250 -0.5939 0.05843 0.05312 -0.0349 1.0000 0.0177
-7.000 -0.5981 0.05507 0.04958 -0.0322 1.0000 0.0174
-6.750 -0.5992 0.05174 0.04604 -0.0295 1.0000 0.0171
-6.500 -0.5974 0.04846 0.04251 -0.0269 1.0000 0.0169
-6.250 -0.5921 0.04538 0.03911 -0.0243 1.0000 0.0170
-6.000 -0.5831 0.04267 0.03602 -0.0218 1.0000 0.0175
-5.750 -0.5708 0.04071 0.03363 -0.0194 1.0000 0.0182
-5.500 -0.5599 0.03748 0.02997 -0.0172 1.0000 0.0187
-5.250 -0.5453 0.03447 0.02654 -0.0154 1.0000 0.0189
-5.000 -0.5191 0.03164 0.02323 -0.0153 0.9979 0.0189
-4.750 -0.4901 0.02880 0.01986 -0.0157 0.9957 0.0191
-4.500 -0.4605 0.02634 0.01705 -0.0160 0.9936 0.0197
-4.250 -0.4306 0.02438 0.01488 -0.0165 0.9912 0.0207
-4.000 -0.4001 0.02311 0.01347 -0.0173 0.9887 0.0242
-3.750 -0.3688 0.02185 0.01207 -0.0180 0.9865 0.0272
-3.500 -0.3405 0.02072 0.01078 -0.0182 0.9831 0.0293
-3.250 -0.3110 0.01959 0.00952 -0.0189 0.9799 0.0352
-3.000 -0.2784 0.01882 0.00854 -0.0201 0.9772 0.0477
-2.750 -0.2544 0.01673 0.00764 -0.0204 0.9740 0.2796
-2.500 -0.2381 0.01497 0.00793 -0.0174 0.9715 0.7297
-2.250 -0.2083 0.01524 0.00856 -0.0147 0.9703 0.8997
-2.000 -0.1652 0.01542 0.00844 -0.0178 0.9683 0.9269
-1.750 -0.1183 0.01558 0.00830 -0.0220 0.9667 0.9469
-1.500 -0.0760 0.01567 0.00818 -0.0254 0.9633 0.9646
-1.250 -0.0296 0.01575 0.00807 -0.0298 0.9606 0.9779
-1.000 0.0195 0.01581 0.00794 -0.0348 0.9584 0.9885
-0.750 0.0695 0.01584 0.00783 -0.0401 0.9563 0.9980
-0.500 0.1026 0.01581 0.00772 -0.0420 0.9502 1.0000
-0.250 0.1347 0.01578 0.00760 -0.0435 0.9438 1.0000
0.000 0.1661 0.01576 0.00753 -0.0448 0.9372 1.0000
0.250 0.1987 0.01573 0.00747 -0.0463 0.9306 1.0000
0.500 0.2297 0.01571 0.00743 -0.0474 0.9234 1.0000
0.750 0.2636 0.01566 0.00739 -0.0490 0.9168 1.0000
1.000 0.2911 0.01564 0.00738 -0.0493 0.9081 1.0000
1.250 0.3266 0.01555 0.00735 -0.0510 0.9021 1.0000
1.500 0.3514 0.01553 0.00737 -0.0506 0.8921 1.0000
1.750 0.3820 0.01546 0.00737 -0.0512 0.8842 1.0000
2.000 0.4121 0.01537 0.00737 -0.0517 0.8757 1.0000
2.250 0.4370 0.01534 0.00746 -0.0512 0.8650 1.0000
2.500 0.4637 0.01527 0.00751 -0.0509 0.8546 1.0000
2.750 0.4920 0.01517 0.00754 -0.0508 0.8441 1.0000
3.000 0.5202 0.01505 0.00757 -0.0507 0.8326 1.0000
3.250 0.5458 0.01495 0.00768 -0.0499 0.8185 1.0000
3.500 0.5706 0.01486 0.00776 -0.0490 0.8023 1.0000
3.750 0.5969 0.01475 0.00785 -0.0483 0.7851 1.0000
4.000 0.6252 0.01435 0.00759 -0.0472 0.7479 1.0000
4.250 0.6510 0.01415 0.00654 -0.0440 0.5520 1.0000
4.500 0.6583 0.01539 0.00685 -0.0398 0.3773 1.0000
4.750 0.6580 0.01771 0.00772 -0.0353 0.1240 1.0000
5.000 0.6680 0.01942 0.00885 -0.0324 0.0493 1.0000
5.250 0.6828 0.02060 0.01009 -0.0300 0.0389 1.0000
5.500 0.7000 0.02148 0.01116 -0.0280 0.0315 1.0000
5.750 0.7124 0.02289 0.01265 -0.0254 0.0268 1.0000
6.000 0.7279 0.02432 0.01419 -0.0230 0.0251 1.0000
6.250 0.7476 0.02588 0.01589 -0.0214 0.0233 1.0000
6.500 0.7693 0.02733 0.01748 -0.0203 0.0200 1.0000
6.750 0.7917 0.02914 0.01953 -0.0194 0.0180 1.0000
7.000 0.8153 0.03159 0.02218 -0.0186 0.0171 1.0000
7.250 0.8370 0.03460 0.02549 -0.0175 0.0165 1.0000
7.500 0.8546 0.03800 0.02928 -0.0159 0.0161 1.0000
7.750 0.8679 0.04145 0.03316 -0.0137 0.0160 1.0000
8.250 0.8828 0.04752 0.04009 -0.0080 0.0152 1.0000
8.500 0.8881 0.05010 0.04311 -0.0050 0.0146 1.0000
8.750 0.8893 0.05313 0.04653 -0.0019 0.0141 1.0000
9.000 0.8865 0.05641 0.05014 0.0012 0.0139 1.0000
9.250 0.8796 0.05978 0.05380 0.0044 0.0138 1.0000
9.500 0.8678 0.06299 0.05725 0.0077 0.0138 1.0000
9.750 0.8533 0.06632 0.06077 0.0106 0.0139 1.0000
10.000 0.8373 0.06995 0.06458 0.0124 0.0140 1.0000
10.250 0.8204 0.07404 0.06883 0.0130 0.0141 1.0000
10.500 0.8029 0.07872 0.07364 0.0123 0.0142 1.0000
10.750 0.7855 0.08416 0.07920 0.0100 0.0143 1.0000
11.000 0.7693 0.09053 0.08566 0.0062 0.0144 1.0000
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Polar data table (+)
Polar graphs
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