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N-10 (n10-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: N-10 (n10-il)
Reynolds number: 50,000
Max Cl/Cd: 37.22 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n10-il-50000-n5.txt
Download as CSV file: xf-n10-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: N-10                                            
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.3912   0.10419   0.09704  -0.0393   0.9999   0.0803
 -10.750  -0.3821   0.10075   0.09361  -0.0382   0.9999   0.0788
 -10.500  -0.3839   0.09730   0.09023  -0.0387   0.9999   0.0783
 -10.250  -0.3893   0.09394   0.08697  -0.0392   0.9999   0.0781
 -10.000  -0.3978   0.09074   0.08388  -0.0393   0.9999   0.0779
  -9.750  -0.4078   0.08750   0.08076  -0.0395   0.9999   0.0776
  -9.500  -0.4156   0.08385   0.07720  -0.0405   0.9999   0.0773
  -9.250  -0.4233   0.08010   0.07352  -0.0413   0.9999   0.0767
  -9.000  -0.4309   0.07620   0.06966  -0.0420   0.9999   0.0759
  -8.750  -0.4380   0.07209   0.06555  -0.0427   0.9999   0.0751
  -8.500  -0.4436   0.06780   0.06121  -0.0434   0.9999   0.0743
  -8.250  -0.4466   0.06338   0.05666  -0.0441   0.9999   0.0737
  -8.000  -0.4459   0.05908   0.05218  -0.0447   0.9999   0.0737
  -7.750  -0.4411   0.05521   0.04806  -0.0452   0.9999   0.0749
  -7.500  -0.4329   0.05132   0.04382  -0.0457   0.9999   0.0765
  -7.250  -0.4211   0.04753   0.03957  -0.0462   0.9999   0.0774
  -7.000  -0.4060   0.04418   0.03578  -0.0465   0.9999   0.0778
  -6.750  -0.3731   0.04051   0.03145  -0.0496   0.9950   0.0787
  -6.500  -0.3379   0.03753   0.02768  -0.0524   0.9892   0.0808
  -6.250  -0.3040   0.03575   0.02583  -0.0548   0.9838   0.0843
  -6.000  -0.2699   0.03403   0.02378  -0.0567   0.9775   0.0873
  -5.750  -0.2339   0.03233   0.02166  -0.0587   0.9719   0.0897
  -5.500  -0.1989   0.03091   0.01984  -0.0603   0.9655   0.0926
  -5.250  -0.1633   0.02971   0.01838  -0.0619   0.9596   0.0965
  -5.000  -0.1302   0.02885   0.01747  -0.0633   0.9525   0.1033
  -4.750  -0.0938   0.02800   0.01638  -0.0649   0.9466   0.1108
  -4.500  -0.0620   0.02723   0.01562  -0.0659   0.9390   0.1184
  -4.250  -0.0231   0.02653   0.01488  -0.0681   0.9338   0.1329
  -4.000   0.0066   0.02604   0.01449  -0.0688   0.9248   0.1557
  -3.750   0.0464   0.02541   0.01404  -0.0713   0.9189   0.2084
  -3.500   0.0777   0.02462   0.01367  -0.0724   0.9085   0.2959
  -3.250   0.1128   0.02348   0.01337  -0.0738   0.8984   0.4599
  -3.000   0.1561   0.02182   0.01307  -0.0738   0.8893   0.8835
  -2.750   0.2078   0.02146   0.01231  -0.0778   0.8748   1.0001
  -2.500   0.2438   0.02130   0.01182  -0.0788   0.8608   1.0001
  -2.250   0.2757   0.02128   0.01153  -0.0793   0.8482   1.0001
  -2.000   0.3076   0.02128   0.01130  -0.0799   0.8371   1.0001
  -1.750   0.3437   0.02119   0.01099  -0.0810   0.8276   1.0001
  -1.250   0.3993   0.02134   0.01082  -0.0806   0.8017   1.0001
  -1.000   0.4279   0.02140   0.01074  -0.0804   0.7889   1.0001
  -0.750   0.4569   0.02143   0.01065  -0.0803   0.7758   1.0001
  -0.500   0.4856   0.02145   0.01056  -0.0800   0.7624   1.0001
  -0.250   0.5135   0.02148   0.01050  -0.0797   0.7483   1.0001
   0.000   0.5401   0.02154   0.01048  -0.0791   0.7331   1.0001
   0.250   0.5659   0.02162   0.01048  -0.0784   0.7169   1.0001
   0.500   0.5918   0.02170   0.01051  -0.0777   0.7002   1.0001
   0.750   0.6183   0.02178   0.01051  -0.0771   0.6833   1.0001
   1.000   0.6452   0.02185   0.01052  -0.0765   0.6661   1.0001
   1.250   0.6724   0.02195   0.01054  -0.0760   0.6485   1.0001
   1.500   0.6996   0.02208   0.01059  -0.0755   0.6308   1.0001
   1.750   0.7266   0.02228   0.01070  -0.0750   0.6133   1.0001
   2.000   0.7530   0.02254   0.01091  -0.0745   0.5962   1.0001
   2.250   0.7783   0.02290   0.01121  -0.0740   0.5792   1.0001
   2.500   0.8031   0.02329   0.01158  -0.0735   0.5627   1.0001
   2.750   0.8281   0.02370   0.01198  -0.0730   0.5475   1.0001
   3.000   0.8532   0.02413   0.01240  -0.0726   0.5338   1.0001
   3.250   0.8775   0.02464   0.01295  -0.0721   0.5210   1.0001
   3.500   0.9021   0.02516   0.01352  -0.0718   0.5094   1.0001
   3.750   0.9275   0.02565   0.01403  -0.0714   0.4991   1.0001
   4.000   0.9530   0.02609   0.01446  -0.0711   0.4885   1.0001
   4.250   0.9757   0.02662   0.01507  -0.0704   0.4761   1.0001
   4.500   0.9982   0.02709   0.01556  -0.0695   0.4626   1.0001
   4.750   1.0199   0.02753   0.01600  -0.0685   0.4479   1.0001
   5.000   1.0411   0.02801   0.01647  -0.0675   0.4329   1.0001
   5.250   1.0626   0.02858   0.01710  -0.0666   0.4198   1.0001
   5.500   1.0857   0.02917   0.01774  -0.0660   0.4090   1.0001
   5.750   1.1082   0.02983   0.01848  -0.0653   0.3984   1.0001
   6.000   1.1285   0.03060   0.01942  -0.0645   0.3878   1.0001
   6.250   1.1502   0.03131   0.02025  -0.0637   0.3772   1.0001
   6.500   1.1718   0.03200   0.02103  -0.0629   0.3659   1.0001
   6.750   1.1884   0.03287   0.02210  -0.0616   0.3536   1.0001
   7.000   1.2056   0.03373   0.02312  -0.0603   0.3412   1.0001
   7.250   1.2234   0.03457   0.02413  -0.0591   0.3291   1.0001
   7.500   1.2424   0.03537   0.02503  -0.0580   0.3172   1.0001
   7.750   1.2550   0.03645   0.02635  -0.0562   0.3043   1.0001
   8.000   1.2667   0.03757   0.02769  -0.0543   0.2915   1.0001
   8.250   1.2781   0.03871   0.02902  -0.0524   0.2791   1.0001
   8.500   1.2897   0.03982   0.03027  -0.0506   0.2677   1.0001
   8.750   1.3016   0.04092   0.03155  -0.0488   0.2573   1.0001
   9.000   1.3053   0.04241   0.03329  -0.0462   0.2468   1.0001
   9.250   1.3073   0.04369   0.03472  -0.0435   0.2364   1.0001
   9.500   1.3073   0.04489   0.03600  -0.0408   0.2255   1.0001
   9.750   1.3046   0.04629   0.03748  -0.0382   0.2143   1.0001
  10.000   1.2978   0.04836   0.03968  -0.0360   0.2026   1.0001
  10.250   1.2909   0.05066   0.04205  -0.0343   0.1911   1.0001
  10.500   1.2837   0.05325   0.04467  -0.0331   0.1798   1.0001
  10.750   1.2757   0.05617   0.04758  -0.0322   0.1686   1.0001
  11.000   1.2665   0.05944   0.05082  -0.0317   0.1577   1.0001
  11.250   1.2557   0.06334   0.05486  -0.0317   0.1473   1.0001
  11.500   1.2446   0.06762   0.05927  -0.0322   0.1379   1.0001
  11.750   1.2351   0.07171   0.06338  -0.0326   0.1296   1.0001
  12.000   1.2228   0.07670   0.06863  -0.0337   0.1211   1.0001
  12.250   1.2112   0.08155   0.07357  -0.0348   0.1131   1.0001
  12.500   1.1979   0.08700   0.07920  -0.0365   0.1043   1.0001
  12.750   1.1841   0.09283   0.08519  -0.0384   0.0954   1.0001
  13.000   1.1715   0.09852   0.09095  -0.0404   0.0866   1.0001
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