NACA/LANGLEY SYMMETRICAL (n0011sc-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA/LANGLEY SYMMETRICAL (n0011sc-il) Reynolds number: 100,000 Max Cl/Cd: 30.36 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n0011sc-il-100000.txt Download as CSV file: xf-n0011sc-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NACA/LANGLEY SYMMETRICAL
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 -0.5833 0.09819 0.09261 -0.0231 1.0000 0.1650
-9.500 -0.5830 0.09502 0.08947 -0.0226 1.0000 0.1693
-9.250 -0.6637 0.08861 0.08319 -0.0282 1.0000 0.1757
-9.000 -0.7235 0.08651 0.08108 -0.0226 1.0000 0.1762
-8.750 -0.6462 0.08147 0.07611 -0.0247 1.0000 0.1823
-8.500 -0.6643 0.07843 0.07311 -0.0223 1.0000 0.1860
-8.250 -0.7066 0.07606 0.07075 -0.0169 1.0000 0.1896
-8.000 -0.8789 0.05287 0.04534 0.0001 1.0000 0.0879
-7.750 -0.8730 0.04921 0.04160 0.0029 1.0000 0.0868
-7.500 -0.8692 0.04603 0.03822 0.0064 1.0000 0.0857
-7.250 -0.8660 0.04301 0.03489 0.0103 1.0000 0.0847
-7.000 -0.8607 0.04023 0.03177 0.0141 1.0000 0.0841
-6.750 -0.8531 0.03774 0.02890 0.0178 1.0000 0.0842
-6.500 -0.8430 0.03572 0.02649 0.0212 1.0000 0.0854
-6.250 -0.8315 0.03399 0.02433 0.0245 1.0000 0.0872
-6.000 -0.8168 0.03211 0.02209 0.0272 1.0000 0.0887
-5.750 -0.7964 0.03019 0.02012 0.0285 1.0000 0.0908
-5.500 -0.7762 0.02894 0.01878 0.0300 1.0000 0.0939
-5.250 -0.7565 0.02788 0.01752 0.0318 1.0000 0.0983
-5.000 -0.7338 0.02648 0.01599 0.0329 1.0000 0.1027
-4.750 -0.7114 0.02544 0.01498 0.0340 1.0000 0.1081
-4.500 -0.6898 0.02454 0.01392 0.0354 1.0000 0.1153
-4.250 -0.6671 0.02348 0.01302 0.0364 1.0000 0.1235
-4.000 -0.6458 0.02254 0.01213 0.0377 1.0000 0.1337
-3.750 -0.6259 0.02169 0.01136 0.0394 1.0000 0.1474
-3.500 -0.6081 0.02086 0.01069 0.0413 1.0000 0.1657
-3.250 -0.5917 0.02007 0.01007 0.0436 1.0000 0.1920
-3.000 -0.5782 0.01907 0.00949 0.0464 1.0000 0.2346
-2.750 -0.4287 0.01851 0.01216 0.0267 1.0000 0.8851
-2.500 -0.3454 0.02068 0.01402 0.0186 1.0000 0.9303
-2.250 -0.2487 0.02211 0.01516 0.0066 1.0000 0.9611
-2.000 -0.1375 0.02252 0.01531 -0.0095 1.0000 0.9867
-1.750 -0.0696 0.02224 0.01488 -0.0183 1.0000 1.0000
-1.500 -0.0600 0.02197 0.01457 -0.0158 1.0000 1.0000
-1.250 -0.0502 0.02174 0.01431 -0.0132 1.0000 1.0000
-1.000 -0.0404 0.02157 0.01411 -0.0106 1.0000 1.0000
-0.750 -0.0303 0.02143 0.01395 -0.0080 1.0000 1.0000
-0.500 -0.0203 0.02134 0.01384 -0.0053 1.0000 1.0000
-0.250 -0.0102 0.02128 0.01377 -0.0027 1.0000 1.0000
0.000 0.0000 0.02126 0.01375 0.0000 1.0000 1.0000
0.250 0.0101 0.02128 0.01377 0.0027 1.0000 1.0000
0.500 0.0203 0.02133 0.01384 0.0053 1.0000 1.0000
0.750 0.0304 0.02143 0.01395 0.0080 1.0000 1.0000
1.000 0.0404 0.02156 0.01410 0.0106 1.0000 1.0000
1.250 0.0503 0.02174 0.01431 0.0132 1.0000 1.0000
1.500 0.0600 0.02196 0.01456 0.0158 1.0000 1.0000
1.750 0.0696 0.02223 0.01487 0.0183 1.0000 1.0000
2.000 0.1409 0.02251 0.01531 0.0089 0.9860 1.0000
2.250 0.2459 0.02212 0.01516 -0.0061 0.9615 1.0000
2.500 0.3454 0.02068 0.01402 -0.0186 0.9306 1.0000
2.750 0.4285 0.01851 0.01215 -0.0266 0.8849 1.0000
3.000 0.5783 0.01905 0.00948 -0.0464 0.2361 1.0000
3.250 0.5916 0.02006 0.01007 -0.0436 0.1917 1.0000
3.500 0.6080 0.02085 0.01068 -0.0413 0.1654 1.0000
3.750 0.6258 0.02169 0.01136 -0.0394 0.1474 1.0000
4.000 0.6457 0.02254 0.01213 -0.0377 0.1339 1.0000
4.250 0.6670 0.02348 0.01302 -0.0364 0.1232 1.0000
4.500 0.6898 0.02457 0.01394 -0.0355 0.1151 1.0000
4.750 0.7116 0.02546 0.01501 -0.0340 0.1082 1.0000
5.000 0.7337 0.02647 0.01598 -0.0329 0.1027 1.0000
5.250 0.7560 0.02784 0.01749 -0.0317 0.0980 1.0000
5.500 0.7761 0.02894 0.01878 -0.0299 0.0940 1.0000
5.750 0.7963 0.03019 0.02012 -0.0284 0.0908 1.0000
6.000 0.8167 0.03212 0.02210 -0.0272 0.0887 1.0000
6.250 0.8312 0.03398 0.02432 -0.0244 0.0871 1.0000
6.500 0.8426 0.03565 0.02644 -0.0211 0.0851 1.0000
6.750 0.8528 0.03774 0.02890 -0.0178 0.0840 1.0000
7.000 0.8604 0.04025 0.03178 -0.0141 0.0840 1.0000
7.250 0.8655 0.04305 0.03494 -0.0102 0.0846 1.0000
7.500 0.8690 0.04603 0.03821 -0.0063 0.0856 1.0000
7.750 0.8726 0.04922 0.04161 -0.0028 0.0868 1.0000
8.000 0.8781 0.05295 0.04544 0.0000 0.0878 1.0000
8.250 0.7051 0.07603 0.07072 0.0169 0.1893 1.0000
8.500 0.6644 0.07841 0.07309 0.0223 0.1856 1.0000
8.750 0.6495 0.08138 0.07603 0.0248 0.1819 1.0000
9.000 0.7231 0.08653 0.08110 0.0226 0.1762 1.0000
9.250 0.6653 0.08869 0.08327 0.0281 0.1758 1.0000
9.500 0.5838 0.09495 0.08941 0.0226 0.1692 1.0000
9.750 0.5850 0.09807 0.09249 0.0233 0.1648 1.0000
10.000 0.6650 0.09891 0.09339 0.0324 0.1602 1.0000
10.250 0.5854 0.10591 0.10028 0.0241 0.1587 1.0000
10.500 0.5596 0.11014 0.10439 0.0207 0.1519 1.0000
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Polar data table (+)
Polar graphs
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