NACA 16009 (naca16009-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 16009 (naca16009-il) Reynolds number: 100,000 Max Cl/Cd: 28.82 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca16009-il-100000-n5.txt Download as CSV file: xf-naca16009-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 16009
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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.4783 0.11250 0.10752 -0.0262 1.0000 0.0268
-11.000 -0.4820 0.10825 0.10330 -0.0271 1.0000 0.0257
-10.750 -0.5956 0.11125 0.10605 -0.0219 1.0000 0.0284
-10.500 -0.5962 0.10703 0.10185 -0.0224 1.0000 0.0267
-10.250 -0.5992 0.10224 0.09711 -0.0243 1.0000 0.0255
-10.000 -0.6041 0.09710 0.09202 -0.0267 1.0000 0.0245
-9.750 -0.6110 0.09150 0.08647 -0.0300 1.0000 0.0237
-9.500 -0.6218 0.08544 0.08045 -0.0342 1.0000 0.0231
-9.250 -0.6368 0.08031 0.07531 -0.0361 1.0000 0.0225
-9.000 -0.6551 0.07615 0.07111 -0.0353 1.0000 0.0220
-8.750 -0.6757 0.07258 0.06750 -0.0323 1.0000 0.0215
-8.500 -0.6950 0.06785 0.06270 -0.0290 1.0000 0.0204
-8.250 -0.7041 0.06408 0.05867 -0.0252 1.0000 0.0194
-7.750 -0.7105 0.05837 0.05248 -0.0182 1.0000 0.0187
-7.500 -0.7160 0.05483 0.04874 -0.0144 1.0000 0.0185
-7.250 -0.7191 0.05141 0.04509 -0.0105 1.0000 0.0184
-7.000 -0.7198 0.04808 0.04147 -0.0066 1.0000 0.0182
-6.750 -0.7180 0.04483 0.03789 -0.0028 1.0000 0.0181
-6.500 -0.7134 0.04168 0.03437 0.0010 1.0000 0.0181
-6.250 -0.7060 0.03868 0.03095 0.0045 1.0000 0.0181
-6.000 -0.6955 0.03585 0.02767 0.0077 1.0000 0.0183
-5.750 -0.6819 0.03326 0.02462 0.0105 1.0000 0.0185
-5.500 -0.6657 0.03081 0.02172 0.0130 1.0000 0.0192
-5.250 -0.6499 0.02852 0.01922 0.0146 1.0000 0.0218
-5.000 -0.6300 0.02701 0.01747 0.0162 1.0000 0.0243
-4.750 -0.6066 0.02509 0.01524 0.0175 1.0000 0.0252
-4.500 -0.5835 0.02346 0.01340 0.0187 1.0000 0.0264
-4.250 -0.5622 0.02211 0.01188 0.0202 1.0000 0.0279
-4.000 -0.5426 0.02103 0.01055 0.0220 1.0000 0.0297
-3.750 -0.5251 0.01986 0.00932 0.0239 1.0000 0.0336
-3.500 -0.5059 0.01912 0.00853 0.0255 1.0000 0.0445
-3.250 -0.4867 0.01827 0.00771 0.0272 1.0000 0.0684
-3.000 -0.4689 0.01702 0.00705 0.0287 1.0000 0.1627
-2.750 -0.4256 0.01477 0.00785 0.0273 1.0000 0.8316
-2.500 -0.3773 0.01581 0.00858 0.0250 1.0000 0.9139
-2.250 -0.2313 0.01759 0.00977 0.0029 1.0000 0.9700
-2.000 -0.1905 0.01749 0.00948 -0.0004 1.0000 0.9769
-1.750 -0.1550 0.01739 0.00918 -0.0027 1.0000 0.9835
-1.500 -0.1191 0.01725 0.00892 -0.0051 1.0000 0.9888
-1.250 -0.0853 0.01715 0.00873 -0.0071 1.0000 0.9943
-1.000 -0.0505 0.01702 0.00853 -0.0093 1.0000 0.9987
-0.750 -0.0327 0.01695 0.00841 -0.0081 1.0000 1.0000
-0.500 -0.0218 0.01690 0.00834 -0.0054 1.0000 1.0000
-0.250 -0.0109 0.01687 0.00830 -0.0027 1.0000 1.0000
0.000 0.0000 0.01686 0.00829 0.0000 1.0000 1.0000
0.250 0.0109 0.01687 0.00830 0.0027 1.0000 1.0000
0.500 0.0218 0.01690 0.00834 0.0054 1.0000 1.0000
0.750 0.0327 0.01695 0.00841 0.0081 1.0000 1.0000
1.000 0.0505 0.01702 0.00853 0.0093 0.9987 1.0000
1.250 0.0852 0.01715 0.00873 0.0071 0.9943 1.0000
1.500 0.1190 0.01724 0.00892 0.0051 0.9888 1.0000
1.750 0.1550 0.01739 0.00918 0.0027 0.9835 1.0000
2.000 0.1905 0.01749 0.00947 0.0004 0.9769 1.0000
2.250 0.2313 0.01759 0.00976 -0.0029 0.9700 1.0000
2.500 0.3773 0.01580 0.00858 -0.0250 0.9139 1.0000
2.750 0.4256 0.01477 0.00785 -0.0273 0.8316 1.0000
3.000 0.4688 0.01702 0.00705 -0.0287 0.1631 1.0000
3.250 0.4866 0.01826 0.00771 -0.0272 0.0684 1.0000
3.500 0.5058 0.01912 0.00853 -0.0255 0.0443 1.0000
3.750 0.5250 0.01986 0.00932 -0.0239 0.0336 1.0000
4.000 0.5425 0.02102 0.01054 -0.0220 0.0297 1.0000
4.250 0.5621 0.02210 0.01188 -0.0202 0.0279 1.0000
4.500 0.5834 0.02345 0.01339 -0.0187 0.0264 1.0000
4.750 0.6065 0.02508 0.01524 -0.0174 0.0252 1.0000
5.000 0.6299 0.02701 0.01746 -0.0161 0.0243 1.0000
5.250 0.6498 0.02850 0.01921 -0.0146 0.0218 1.0000
5.500 0.6656 0.03080 0.02172 -0.0129 0.0191 1.0000
5.750 0.6818 0.03325 0.02461 -0.0105 0.0185 1.0000
6.000 0.6954 0.03584 0.02766 -0.0077 0.0183 1.0000
6.250 0.7059 0.03867 0.03094 -0.0045 0.0181 1.0000
6.500 0.7134 0.04167 0.03436 -0.0010 0.0181 1.0000
6.750 0.7179 0.04482 0.03787 0.0028 0.0181 1.0000
7.000 0.7197 0.04807 0.04146 0.0066 0.0182 1.0000
7.250 0.7191 0.05140 0.04508 0.0105 0.0184 1.0000
7.500 0.7160 0.05482 0.04873 0.0144 0.0185 1.0000
7.750 0.7105 0.05836 0.05247 0.0182 0.0187 1.0000
8.250 0.7041 0.06407 0.05866 0.0252 0.0194 1.0000
8.500 0.6951 0.06787 0.06271 0.0290 0.0204 1.0000
8.750 0.6758 0.07259 0.06751 0.0322 0.0215 1.0000
9.000 0.6553 0.07616 0.07113 0.0353 0.0220 1.0000
9.250 0.6371 0.08035 0.07535 0.0361 0.0226 1.0000
9.500 0.6222 0.08549 0.08050 0.0341 0.0231 1.0000
9.750 0.6115 0.09155 0.08652 0.0298 0.0237 1.0000
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Polar data table (+)
Polar graphs
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