NACA-0009 9.0% smoothed (n0009sm-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA-0009 9.0% smoothed (n0009sm-il) Reynolds number: 100,000 Max Cl/Cd: 37.3 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n0009sm-il-100000.txt Download as CSV file: xf-n0009sm-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NACA-0009 9.0% smoothed
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 -0.6402 0.09783 0.09278 -0.0047 1.0000 0.1611
-9.500 -0.7228 0.07389 0.06897 -0.0257 1.0000 0.0911
-9.250 -0.7280 0.07174 0.06685 -0.0244 1.0000 0.0992
-9.000 -0.8160 0.05631 0.05037 -0.0241 1.0000 0.0670
-8.750 -0.8199 0.05152 0.04526 -0.0220 1.0000 0.0667
-8.500 -0.8242 0.04803 0.04118 -0.0189 1.0000 0.0677
-8.250 -0.8075 0.04520 0.03868 -0.0187 1.0000 0.0739
-8.000 -0.8037 0.04147 0.03449 -0.0160 1.0000 0.0757
-7.750 -0.7970 0.03798 0.03045 -0.0132 1.0000 0.0777
-7.500 -0.7890 0.03532 0.02710 -0.0102 1.0000 0.0816
-7.250 -0.7711 0.03273 0.02452 -0.0090 1.0000 0.0861
-7.000 -0.7540 0.03062 0.02204 -0.0071 1.0000 0.0904
-6.750 -0.7372 0.02863 0.01959 -0.0051 1.0000 0.0958
-6.500 -0.7158 0.02676 0.01761 -0.0039 1.0000 0.1004
-6.250 -0.6939 0.02517 0.01574 -0.0025 1.0000 0.1053
-6.000 -0.6719 0.02363 0.01415 -0.0014 1.0000 0.1123
-5.750 -0.6496 0.02250 0.01283 -0.0001 1.0000 0.1202
-5.500 -0.6265 0.02104 0.01145 0.0008 1.0000 0.1273
-5.250 -0.6042 0.01990 0.01027 0.0021 1.0000 0.1373
-5.000 -0.5836 0.01889 0.00933 0.0035 1.0000 0.1519
-4.750 -0.5639 0.01787 0.00846 0.0051 1.0000 0.1707
-4.500 -0.5459 0.01676 0.00758 0.0071 1.0000 0.2011
-4.250 -0.5316 0.01542 0.00682 0.0095 1.0000 0.2743
-4.000 -0.5198 0.01424 0.00639 0.0125 1.0000 0.3983
-3.750 -0.5050 0.01356 0.00614 0.0152 1.0000 0.4932
-3.500 -0.4884 0.01309 0.00595 0.0179 1.0000 0.5720
-3.250 -0.4707 0.01273 0.00586 0.0206 1.0000 0.6441
-3.000 -0.4511 0.01247 0.00584 0.0232 1.0000 0.7119
-2.750 -0.4276 0.01237 0.00591 0.0252 1.0000 0.7777
-2.500 -0.3961 0.01253 0.00614 0.0261 1.0000 0.8439
-2.250 -0.3457 0.01306 0.00661 0.0235 1.0000 0.8996
-2.000 -0.2781 0.01364 0.00698 0.0169 1.0000 0.9314
-1.750 -0.2084 0.01399 0.00711 0.0092 1.0000 0.9547
-1.500 -0.1341 0.01406 0.00699 0.0001 1.0000 0.9730
-1.250 -0.0629 0.01388 0.00666 -0.0089 1.0000 0.9911
-1.000 -0.0197 0.01352 0.00623 -0.0132 1.0000 1.0000
-0.750 -0.0138 0.01323 0.00594 -0.0103 1.0000 1.0000
-0.500 -0.0085 0.01303 0.00575 -0.0071 1.0000 1.0000
-0.250 -0.0040 0.01291 0.00563 -0.0036 1.0000 1.0000
0.000 0.0000 0.01287 0.00559 0.0000 1.0000 1.0000
0.250 0.0040 0.01291 0.00563 0.0036 1.0000 1.0000
0.500 0.0085 0.01303 0.00575 0.0071 1.0000 1.0000
0.750 0.0138 0.01323 0.00594 0.0103 1.0000 1.0000
1.000 0.0197 0.01352 0.00623 0.0132 1.0000 1.0000
1.250 0.0628 0.01387 0.00665 0.0090 0.9911 1.0000
1.500 0.1342 0.01406 0.00699 -0.0001 0.9730 1.0000
1.750 0.2086 0.01399 0.00710 -0.0093 0.9546 1.0000
2.000 0.2783 0.01363 0.00698 -0.0170 0.9314 1.0000
2.250 0.3459 0.01306 0.00661 -0.0235 0.8995 1.0000
2.500 0.3960 0.01253 0.00614 -0.0261 0.8439 1.0000
2.750 0.4275 0.01237 0.00591 -0.0252 0.7775 1.0000
3.000 0.4510 0.01247 0.00583 -0.0231 0.7118 1.0000
3.250 0.4705 0.01273 0.00586 -0.0206 0.6438 1.0000
3.500 0.4883 0.01309 0.00595 -0.0179 0.5719 1.0000
3.750 0.5049 0.01356 0.00614 -0.0152 0.4935 1.0000
4.000 0.5197 0.01424 0.00638 -0.0124 0.3979 1.0000
4.250 0.5315 0.01541 0.00681 -0.0095 0.2749 1.0000
4.500 0.5458 0.01676 0.00758 -0.0070 0.2010 1.0000
4.750 0.5638 0.01787 0.00846 -0.0051 0.1704 1.0000
5.000 0.5835 0.01890 0.00933 -0.0035 0.1518 1.0000
5.250 0.6041 0.01990 0.01026 -0.0021 0.1372 1.0000
5.500 0.6264 0.02104 0.01145 -0.0008 0.1274 1.0000
5.750 0.6495 0.02250 0.01282 0.0002 0.1202 1.0000
6.000 0.6719 0.02364 0.01416 0.0015 0.1124 1.0000
6.250 0.6938 0.02517 0.01574 0.0025 0.1054 1.0000
6.500 0.7158 0.02676 0.01761 0.0040 0.1004 1.0000
6.750 0.7371 0.02863 0.01959 0.0051 0.0958 1.0000
7.000 0.7540 0.03063 0.02205 0.0071 0.0905 1.0000
7.250 0.7711 0.03274 0.02453 0.0091 0.0862 1.0000
7.500 0.7891 0.03528 0.02705 0.0102 0.0817 1.0000
7.750 0.7971 0.03798 0.03044 0.0132 0.0777 1.0000
8.000 0.8036 0.04149 0.03451 0.0160 0.0756 1.0000
8.250 0.8073 0.04527 0.03876 0.0187 0.0741 1.0000
8.500 0.8242 0.04805 0.04120 0.0189 0.0677 1.0000
8.750 0.8197 0.05156 0.04531 0.0220 0.0667 1.0000
9.000 0.8155 0.05629 0.05037 0.0242 0.0669 1.0000
9.250 0.8169 0.06167 0.05590 0.0254 0.0680 1.0000
9.500 0.6962 0.09159 0.08675 0.0152 0.1627 1.0000
9.750 0.6376 0.09795 0.09289 0.0041 0.1607 1.0000
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Polar data table (+)
Polar graphs
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