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NACA 6412 (naca6412-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA 6412 (naca6412-il)
Reynolds number: 100,000
Max Cl/Cd: 58.68 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca6412-il-100000-n5.txt
Download as CSV file: xf-naca6412-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 6412                                       
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.2236   0.09620   0.09112  -0.0677   0.9710   0.0459
  -8.500  -0.2154   0.09280   0.08773  -0.0697   0.9635   0.0455
  -8.250  -0.2029   0.08860   0.08351  -0.0739   0.9585   0.0451
  -8.000  -0.1990   0.08491   0.07984  -0.0764   0.9496   0.0449
  -7.750  -0.1884   0.07934   0.07425  -0.0833   0.9428   0.0454
  -7.500  -0.1866   0.07360   0.06850  -0.0894   0.9312   0.0459
  -7.250  -0.1754   0.06601   0.06083  -0.0989   0.9231   0.0462
  -7.000  -0.1643   0.05789   0.05258  -0.1078   0.9136   0.0462
  -6.750  -0.1576   0.04610   0.04034  -0.1182   0.9033   0.0466
  -6.500  -0.1270   0.04635   0.04063  -0.1189   0.8983   0.0479
  -6.250  -0.0987   0.03921   0.03291  -0.1262   0.8941   0.0504
  -6.000  -0.0866   0.03339   0.02624  -0.1280   0.8835   0.0523
  -5.750  -0.0557   0.02982   0.02200  -0.1304   0.8794   0.0543
  -5.500  -0.0312   0.02908   0.02121  -0.1302   0.8721   0.0565
  -5.250  -0.0031   0.02757   0.01935  -0.1308   0.8660   0.0598
  -5.000   0.0304   0.02573   0.01708  -0.1322   0.8623   0.0631
  -4.750   0.0537   0.02513   0.01645  -0.1316   0.8542   0.0659
  -4.250   0.1184   0.02314   0.01406  -0.1333   0.8448   0.0750
  -4.000   0.1406   0.02268   0.01349  -0.1322   0.8355   0.0798
  -3.750   0.1728   0.02187   0.01253  -0.1329   0.8303   0.0857
  -3.500   0.2007   0.02140   0.01199  -0.1328   0.8233   0.0923
  -3.250   0.2288   0.02083   0.01134  -0.1327   0.8159   0.0991
  -3.000   0.2631   0.02024   0.01064  -0.1337   0.8112   0.1083
  -2.750   0.2859   0.01991   0.01031  -0.1327   0.8011   0.1153
  -2.500   0.3187   0.01940   0.00970  -0.1333   0.7955   0.1264
  -2.250   0.3434   0.01917   0.00949  -0.1327   0.7860   0.1374
  -2.000   0.3749   0.01874   0.00905  -0.1331   0.7793   0.1502
  -1.750   0.4007   0.01851   0.00881  -0.1326   0.7700   0.1638
  -1.500   0.4315   0.01818   0.00845  -0.1328   0.7626   0.1804
  -1.250   0.4575   0.01801   0.00829  -0.1324   0.7531   0.1977
  -1.000   0.4884   0.01773   0.00801  -0.1327   0.7454   0.2188
  -0.750   0.5143   0.01761   0.00791  -0.1322   0.7353   0.2405
  -0.500   0.5448   0.01737   0.00766  -0.1325   0.7278   0.2672
  -0.250   0.5702   0.01729   0.00763  -0.1319   0.7175   0.2955
   0.000   0.6018   0.01705   0.00740  -0.1325   0.7100   0.3338
   0.250   0.6271   0.01691   0.00742  -0.1320   0.6994   0.3837
   0.500   0.6551   0.01630   0.00738  -0.1320   0.6914   0.5607
   0.750   0.6956   0.01559   0.00732  -0.1340   0.6816   0.9999
   1.000   0.7237   0.01571   0.00726  -0.1339   0.6731   0.9999
   1.250   0.7501   0.01588   0.00728  -0.1335   0.6637   0.9999
   1.500   0.7772   0.01605   0.00730  -0.1333   0.6552   0.9999
   1.750   0.8038   0.01623   0.00737  -0.1330   0.6465   0.9999
   2.000   0.8305   0.01643   0.00746  -0.1327   0.6384   0.9999
   2.250   0.8566   0.01664   0.00758  -0.1323   0.6300   0.9999
   2.500   0.8835   0.01685   0.00770  -0.1321   0.6224   0.9999
   2.750   0.9087   0.01710   0.00789  -0.1316   0.6142   0.9999
   3.000   0.9364   0.01732   0.00800  -0.1315   0.6076   0.9999
   3.250   0.9604   0.01761   0.00829  -0.1308   0.5993   0.9999
   3.500   0.9880   0.01784   0.00843  -0.1307   0.5929   0.9999
   3.750   1.0118   0.01816   0.00875  -0.1300   0.5852   0.9999
   4.000   1.0377   0.01843   0.00899  -0.1297   0.5783   0.9999
   4.250   1.0635   0.01873   0.00926  -0.1293   0.5719   0.9999
   4.500   1.0873   0.01907   0.00962  -0.1287   0.5646   0.9999
   4.750   1.1146   0.01934   0.00985  -0.1286   0.5589   0.9999
   5.000   1.1371   0.01972   0.01029  -0.1277   0.5518   0.9999
   5.250   1.1619   0.02005   0.01062  -0.1272   0.5452   0.9999
   5.500   1.1877   0.02038   0.01094  -0.1269   0.5393   0.9999
   5.750   1.2094   0.02079   0.01144  -0.1260   0.5320   0.9999
   6.000   1.2353   0.02110   0.01176  -0.1256   0.5261   0.9999
   6.250   1.2574   0.02153   0.01226  -0.1248   0.5193   0.9999
   6.500   1.2801   0.02192   0.01272  -0.1239   0.5124   0.9999
   6.750   1.3057   0.02225   0.01305  -0.1236   0.5064   0.9999
   7.000   1.3247   0.02274   0.01368  -0.1222   0.4989   0.9999
   7.250   1.3492   0.02309   0.01408  -0.1217   0.4924   0.9999
   7.500   1.3684   0.02357   0.01467  -0.1203   0.4847   0.9999
   7.750   1.3896   0.02395   0.01511  -0.1193   0.4767   0.9999
   8.000   1.4083   0.02439   0.01567  -0.1178   0.4683   0.9999
   8.250   1.4274   0.02476   0.01609  -0.1163   0.4589   0.9999
   8.500   1.4408   0.02523   0.01667  -0.1140   0.4476   0.9999
   8.750   1.4549   0.02561   0.01710  -0.1117   0.4356   0.9999
   9.000   1.4671   0.02599   0.01751  -0.1090   0.4229   0.9999
   9.250   1.4729   0.02659   0.01823  -0.1055   0.4095   0.9999
   9.500   1.4799   0.02725   0.01898  -0.1024   0.3961   0.9999
   9.750   1.4869   0.02797   0.01978  -0.0993   0.3822   0.9999
  10.000   1.4931   0.02879   0.02068  -0.0963   0.3678   0.9999
  10.250   1.4979   0.02976   0.02171  -0.0934   0.3521   0.9999
  10.500   1.5015   0.03088   0.02288  -0.0904   0.3350   0.9999
  10.750   1.5034   0.03220   0.02420  -0.0875   0.3163   0.9999
  11.000   1.5029   0.03377   0.02574  -0.0845   0.2963   0.9999
  11.250   1.5010   0.03561   0.02757  -0.0817   0.2744   0.9999
  11.500   1.4960   0.03782   0.02972  -0.0790   0.2518   0.9999
  11.750   1.4894   0.04034   0.03218  -0.0764   0.2292   0.9999
  12.000   1.4805   0.04324   0.03501  -0.0741   0.2071   0.9999
  12.250   1.4704   0.04645   0.03816  -0.0720   0.1864   0.9999
  12.500   1.4596   0.04994   0.04160  -0.0703   0.1671   0.9999
  12.750   1.4484   0.05368   0.04529  -0.0689   0.1502   0.9999
  13.000   1.4377   0.05757   0.04916  -0.0679   0.1354   0.9999
  13.250   1.4275   0.06156   0.05315  -0.0671   0.1225   0.9999
  13.500   1.4181   0.06561   0.05721  -0.0665   0.1116   0.9999
  13.750   1.4088   0.06978   0.06139  -0.0661   0.1025   0.9999
  14.000   1.4004   0.07392   0.06556  -0.0659   0.0945   0.9999
  14.250   1.3937   0.07791   0.06962  -0.0658   0.0874   0.9999
  14.500   1.3853   0.08221   0.07393  -0.0659   0.0817   0.9999
  14.750   1.3812   0.08599   0.07779  -0.0659   0.0760   0.9999
  15.000   1.3748   0.09012   0.08196  -0.0662   0.0716   0.9999
  15.250   1.3711   0.09387   0.08578  -0.0663   0.0673   0.9999
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