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NACA6409 9% (n6409-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA6409 9% (n6409-il)
Reynolds number: 50,000
Max Cl/Cd: 35.96 at α=9°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n6409-il-50000-n5.txt
Download as CSV file: xf-n6409-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA6409 9%                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3232   0.11599   0.10970  -0.0291   1.0000   0.0948
  -7.750  -0.3387   0.11565   0.10948  -0.0273   1.0000   0.0953
  -7.500  -0.3565   0.11541   0.10937  -0.0253   1.0000   0.0956
  -7.250  -0.3696   0.11463   0.10870  -0.0249   1.0000   0.0959
  -7.000  -0.3611   0.11033   0.10445  -0.0253   0.9976   0.0969
  -6.750  -0.3382   0.10532   0.09939  -0.0240   0.9946   0.1024
  -6.500  -0.3222   0.10209   0.09614  -0.0297   0.9865   0.1076
  -6.250  -0.3007   0.09941   0.09341  -0.0452   0.9737   0.1108
  -6.000  -0.2843   0.09449   0.08851  -0.0459   0.9679   0.1118
  -5.750  -0.2660   0.09025   0.08425  -0.0467   0.9616   0.1135
  -5.500  -0.2456   0.08635   0.08032  -0.0505   0.9541   0.1149
  -5.250  -0.2225   0.08238   0.07629  -0.0557   0.9461   0.1159
  -4.750  -0.1438   0.06704   0.06034  -0.0816   0.9298   0.0682
  -4.500  -0.1236   0.06363   0.05687  -0.0833   0.9209   0.0673
  -4.250  -0.0867   0.05896   0.05197  -0.0896   0.9153   0.0661
  -4.000  -0.0561   0.05463   0.04740  -0.0945   0.9064   0.0658
  -3.750  -0.0056   0.04841   0.04053  -0.1040   0.9014   0.0680
  -3.500   0.0265   0.04477   0.03652  -0.1075   0.8933   0.0692
  -3.250   0.0648   0.04167   0.03307  -0.1112   0.8876   0.0706
  -3.000   0.0971   0.03934   0.03036  -0.1134   0.8799   0.0732
  -2.750   0.1365   0.03672   0.02712  -0.1166   0.8737   0.0793
  -2.500   0.1733   0.03438   0.02418  -0.1188   0.8674   0.0834
  -2.250   0.2048   0.03326   0.02286  -0.1198   0.8596   0.0906
  -2.000   0.2408   0.03187   0.02105  -0.1214   0.8533   0.0998
  -1.750   0.2715   0.03097   0.01983  -0.1219   0.8450   0.1120
  -1.500   0.3051   0.03012   0.01877  -0.1228   0.8382   0.1265
  -1.250   0.3364   0.02955   0.01806  -0.1233   0.8300   0.1437
  -1.000   0.3699   0.02903   0.01743  -0.1242   0.8229   0.1662
  -0.750   0.4021   0.02854   0.01685  -0.1248   0.8150   0.1915
  -0.500   0.4337   0.02812   0.01639  -0.1253   0.8072   0.2218
  -0.250   0.4667   0.02768   0.01596  -0.1261   0.7997   0.2618
   0.000   0.4958   0.02733   0.01571  -0.1264   0.7912   0.3104
   0.250   0.5302   0.02657   0.01532  -0.1275   0.7845   0.3963
   0.500   0.5538   0.02523   0.01515  -0.1263   0.7754   1.0000
   0.750   0.5889   0.02522   0.01477  -0.1271   0.7687   1.0000
   1.000   0.6130   0.02555   0.01486  -0.1265   0.7584   1.0000
   1.250   0.6495   0.02546   0.01453  -0.1276   0.7527   1.0000
   1.500   0.6711   0.02589   0.01481  -0.1266   0.7419   1.0000
   1.750   0.7031   0.02596   0.01472  -0.1270   0.7350   1.0000
   2.000   0.7286   0.02626   0.01492  -0.1266   0.7257   1.0000
   2.250   0.7545   0.02658   0.01514  -0.1262   0.7170   1.0000
   2.500   0.7849   0.02671   0.01519  -0.1265   0.7098   1.0000
   2.750   0.8076   0.02718   0.01562  -0.1257   0.7004   1.0000
   3.000   0.8403   0.02723   0.01562  -0.1262   0.6941   1.0000
   3.250   0.8602   0.02784   0.01621  -0.1251   0.6843   1.0000
   3.500   0.8942   0.02785   0.01619  -0.1258   0.6785   1.0000
   3.750   0.9118   0.02859   0.01697  -0.1244   0.6685   1.0000
   4.000   0.9466   0.02857   0.01695  -0.1252   0.6631   1.0000
   4.250   0.9620   0.02943   0.01787  -0.1235   0.6529   1.0000
   4.500   0.9975   0.02940   0.01789  -0.1244   0.6478   1.0000
   4.750   1.0107   0.03039   0.01896  -0.1225   0.6375   1.0000
   5.000   1.0462   0.03036   0.01898  -0.1233   0.6324   1.0000
   5.250   1.0576   0.03146   0.02019  -0.1212   0.6221   1.0000
   5.500   1.0882   0.03167   0.02053  -0.1215   0.6161   1.0000
   5.750   1.1031   0.03263   0.02161  -0.1198   0.6068   1.0000
   6.000   1.1289   0.03309   0.02219  -0.1194   0.5998   1.0000
   6.250   1.1470   0.03390   0.02315  -0.1181   0.5913   1.0000
   6.500   1.1675   0.03462   0.02405  -0.1171   0.5834   1.0000
   6.750   1.1903   0.03520   0.02480  -0.1163   0.5755   1.0000
   7.000   1.2041   0.03625   0.02602  -0.1145   0.5665   1.0000
   7.250   1.2342   0.03643   0.02640  -0.1145   0.5594   1.0000
   7.500   1.2408   0.03782   0.02802  -0.1119   0.5492   1.0000
   7.750   1.2824   0.03735   0.02779  -0.1130   0.5426   1.0000
   8.000   1.2832   0.03893   0.02956  -0.1096   0.5311   1.0000
   8.250   1.2942   0.03988   0.03073  -0.1072   0.5204   1.0000
   8.500   1.3173   0.03968   0.03078  -0.1055   0.5064   1.0000
   8.750   1.3461   0.03773   0.02890  -0.1029   0.4801   1.0000
   9.000   1.3491   0.03752   0.02872  -0.0981   0.4538   1.0000
   9.500   1.3426   0.03931   0.03069  -0.0894   0.4068   1.0000
   9.750   1.3341   0.04111   0.03265  -0.0856   0.3817   1.0000
  10.000   1.3290   0.04275   0.03436  -0.0823   0.3498   1.0000
  10.250   1.3231   0.04467   0.03624  -0.0792   0.3062   1.0000
  10.500   1.3145   0.04708   0.03827  -0.0763   0.2455   1.0000
  10.750   1.2989   0.05072   0.04146  -0.0738   0.1926   1.0000
  11.000   1.2818   0.05507   0.04547  -0.0721   0.1559   1.0000
  11.250   1.2662   0.05963   0.04981  -0.0710   0.1312   1.0000
  11.500   1.2531   0.06417   0.05419  -0.0703   0.1139   1.0000
  11.750   1.2428   0.06853   0.05847  -0.0698   0.1011   1.0000
  12.000   1.2355   0.07264   0.06255  -0.0694   0.0912   1.0000
  12.250   1.2292   0.07667   0.06651  -0.0691   0.0838   1.0000
  12.500   1.2281   0.08011   0.07005  -0.0687   0.0764   1.0000
  12.750   1.2273   0.08345   0.07336  -0.0682   0.0714   1.0000
  13.000   1.2315   0.08622   0.07630  -0.0676   0.0658   1.0000
  13.250   1.2350   0.08901   0.07906  -0.0671   0.0616   1.0000
  13.500   1.2456   0.09097   0.08125  -0.0658   0.0576   1.0000
  13.750   1.2599   0.09251   0.08300  -0.0643   0.0544   1.0000
  14.000   1.2745   0.09403   0.08459  -0.0630   0.0514   1.0000
  14.250   1.2915   0.09563   0.08636  -0.0616   0.0485   1.0000
  14.500   1.2981   0.09882   0.08991  -0.0613   0.0464   1.0000
  14.750   1.3034   0.10228   0.09368  -0.0613   0.0449   1.0000
  15.000   1.3054   0.10627   0.09800  -0.0616   0.0440   1.0000
  15.250   1.3029   0.11088   0.10289  -0.0626   0.0433   1.0000
  15.500   1.2965   0.11610   0.10838  -0.0642   0.0428   1.0000
  15.750   1.2867   0.12196   0.11450  -0.0666   0.0425   1.0000
  16.000   1.2735   0.12860   0.12139  -0.0698   0.0424   1.0000
  16.250   1.2562   0.13636   0.12940  -0.0741   0.0424   1.0000
  16.500   1.2325   0.14615   0.13944  -0.0802   0.0429   1.0000
  16.750   1.2026   0.15880   0.15226  -0.0887   0.0438   1.0000
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