NACA 64(1)-112 (naca641112-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 64(1)-112 (naca641112-il) Reynolds number: 100,000 Max Cl/Cd: 44.13 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca641112-il-100000.txt Download as CSV file: xf-naca641112-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64(1)-112
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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5899 0.09785 0.09297 -0.0138 1.0000 0.1656
-9.750 -0.5751 0.09497 0.09005 -0.0127 1.0000 0.1719
-9.500 -0.5922 0.08974 0.08492 -0.0163 1.0000 0.1807
-9.250 -0.6029 0.08560 0.08085 -0.0190 1.0000 0.1908
-9.000 -0.5898 0.08219 0.07746 -0.0176 1.0000 0.1978
-8.250 -0.7417 0.04964 0.04333 -0.0324 1.0000 0.0939
-8.000 -0.7345 0.04413 0.03695 -0.0299 1.0000 0.0762
-7.750 -0.7210 0.04019 0.03278 -0.0288 1.0000 0.0739
-7.500 -0.7074 0.03692 0.02914 -0.0272 1.0000 0.0720
-7.250 -0.6926 0.03425 0.02611 -0.0254 1.0000 0.0716
-7.000 -0.6776 0.03227 0.02383 -0.0235 1.0000 0.0733
-6.750 -0.6623 0.03041 0.02167 -0.0214 1.0000 0.0746
-6.500 -0.6463 0.02864 0.01964 -0.0194 1.0000 0.0752
-6.250 -0.6303 0.02714 0.01789 -0.0172 1.0000 0.0764
-6.000 -0.6140 0.02571 0.01630 -0.0152 1.0000 0.0783
-5.750 -0.5981 0.02414 0.01486 -0.0136 1.0000 0.0825
-5.500 -0.5829 0.02318 0.01387 -0.0116 1.0000 0.0873
-5.250 -0.5671 0.02233 0.01290 -0.0096 1.0000 0.0911
-5.000 -0.5536 0.02109 0.01186 -0.0076 1.0000 0.0976
-4.750 -0.5399 0.02030 0.01109 -0.0056 1.0000 0.1068
-4.500 -0.5263 0.01948 0.01034 -0.0038 1.0000 0.1191
-4.250 -0.5135 0.01842 0.00951 -0.0021 1.0000 0.1432
-4.000 -0.5022 0.01529 0.00886 -0.0008 0.9959 0.5510
-3.750 -0.4678 0.01613 0.00983 -0.0007 0.9864 0.6501
-3.500 -0.4329 0.01687 0.01051 -0.0011 0.9773 0.6897
-3.250 -0.3977 0.01779 0.01141 -0.0009 0.9691 0.7228
-3.000 -0.3707 0.01892 0.01256 0.0018 0.9598 0.7565
-2.750 -0.3440 0.01992 0.01354 0.0045 0.9512 0.7843
-2.500 -0.3075 0.02039 0.01392 0.0040 0.9442 0.8014
-2.250 -0.2756 0.02037 0.01375 0.0029 0.9353 0.8122
-2.000 -0.2330 0.02039 0.01365 0.0000 0.9293 0.8209
-1.750 -0.2013 0.02037 0.01354 -0.0010 0.9205 0.8294
-1.500 -0.1599 0.02029 0.01334 -0.0040 0.9143 0.8391
-1.250 -0.1293 0.02032 0.01332 -0.0045 0.9058 0.8461
-1.000 -0.0928 0.02019 0.01311 -0.0067 0.8994 0.8552
-0.750 -0.0627 0.02023 0.01311 -0.0073 0.8909 0.8621
-0.500 -0.0276 0.02011 0.01294 -0.0090 0.8844 0.8708
-0.250 0.0014 0.02017 0.01298 -0.0095 0.8760 0.8783
0.000 0.0352 0.02011 0.01290 -0.0108 0.8697 0.8871
0.250 0.0645 0.02017 0.01296 -0.0115 0.8617 0.8958
0.500 0.1005 0.02014 0.01293 -0.0132 0.8552 0.9036
0.750 0.1267 0.02022 0.01302 -0.0134 0.8477 0.9145
1.000 0.1707 0.02026 0.01310 -0.0167 0.8415 0.9209
1.250 0.2091 0.02019 0.01305 -0.0188 0.8367 0.9299
1.500 0.2482 0.02038 0.01332 -0.0218 0.8280 0.9375
1.750 0.2919 0.02028 0.01327 -0.0248 0.8228 0.9454
2.000 0.3359 0.02040 0.01350 -0.0287 0.8140 0.9530
2.250 0.3819 0.02024 0.01342 -0.0321 0.8079 0.9601
2.500 0.4231 0.02036 0.01369 -0.0356 0.7988 0.9690
2.750 0.4708 0.02013 0.01358 -0.0393 0.7922 0.9760
3.000 0.5120 0.02009 0.01369 -0.0423 0.7808 0.9852
3.250 0.5542 0.01924 0.01295 -0.0436 0.7638 0.9934
3.500 0.5863 0.01801 0.01174 -0.0423 0.7373 1.0000
3.750 0.5992 0.01707 0.01074 -0.0378 0.7138 1.0000
4.000 0.6111 0.01653 0.01023 -0.0342 0.6890 1.0000
4.250 0.6250 0.01606 0.00977 -0.0309 0.6665 1.0000
4.500 0.6384 0.01565 0.00940 -0.0277 0.6408 1.0000
4.750 0.6503 0.01527 0.00903 -0.0241 0.6064 1.0000
5.000 0.6593 0.01494 0.00864 -0.0200 0.5477 1.0000
5.250 0.6481 0.01597 0.00833 -0.0128 0.2919 1.0000
5.500 0.6394 0.01866 0.00976 -0.0081 0.1476 1.0000
5.750 0.6499 0.02014 0.01095 -0.0057 0.1199 1.0000
6.000 0.6662 0.02139 0.01207 -0.0041 0.1043 1.0000
6.250 0.6860 0.02270 0.01323 -0.0030 0.0945 1.0000
6.500 0.7099 0.02406 0.01459 -0.0022 0.0868 1.0000
6.750 0.7357 0.02589 0.01623 -0.0021 0.0799 1.0000
7.000 0.7637 0.02758 0.01808 -0.0018 0.0768 1.0000
7.250 0.7907 0.02935 0.02003 -0.0014 0.0734 1.0000
7.500 0.8157 0.03110 0.02185 -0.0012 0.0695 1.0000
7.750 0.8413 0.03382 0.02466 -0.0011 0.0674 1.0000
8.000 0.8645 0.03710 0.02822 -0.0006 0.0669 1.0000
8.250 0.8851 0.03982 0.03130 0.0004 0.0671 1.0000
8.500 0.9031 0.04228 0.03423 0.0018 0.0681 1.0000
8.750 0.9120 0.04565 0.03829 0.0040 0.0696 1.0000
9.000 0.9150 0.05007 0.04335 0.0063 0.0724 1.0000
9.250 0.9168 0.05480 0.04849 0.0080 0.0756 1.0000
9.500 0.8416 0.05152 0.04627 0.0139 0.0858 1.0000
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Polar data table (+)
Polar graphs
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