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N-13 (n13-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: N-13 (n13-il)
Reynolds number: 200,000
Max Cl/Cd: 49.38 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n13-il-200000.txt
Download as CSV file: xf-n13-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: N-13                                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.250  -0.7135   0.11388   0.11001  -0.0219   1.0000   0.0333
 -14.000  -0.7454   0.10172   0.09784  -0.0281   1.0000   0.0325
 -13.750  -0.7881   0.08812   0.08414  -0.0368   1.0000   0.0313
 -13.500  -0.8312   0.07659   0.07242  -0.0447   1.0000   0.0306
 -13.250  -0.8707   0.06768   0.06328  -0.0499   1.0000   0.0296
 -13.000  -0.9048   0.06094   0.05626  -0.0523   1.0000   0.0292
 -12.750  -0.9235   0.05682   0.05196  -0.0526   1.0000   0.0295
 -12.500  -0.9476   0.05254   0.04741  -0.0516   1.0000   0.0293
 -12.250  -0.9652   0.04926   0.04389  -0.0494   1.0000   0.0293
 -12.000  -0.9802   0.04638   0.04076  -0.0463   1.0000   0.0293
 -11.750  -0.9897   0.04414   0.03832  -0.0428   1.0000   0.0297
 -11.500  -0.9987   0.04198   0.03595  -0.0387   1.0000   0.0300
 -11.250  -1.0038   0.04038   0.03415  -0.0345   1.0000   0.0306
 -11.000  -1.0062   0.03886   0.03241  -0.0304   1.0000   0.0317
 -10.750  -1.0056   0.03707   0.03033  -0.0267   1.0000   0.0324
 -10.500  -1.0027   0.03557   0.02853  -0.0231   1.0000   0.0331
 -10.250  -0.9949   0.03291   0.02563  -0.0206   1.0000   0.0342
 -10.000  -0.9810   0.03109   0.02378  -0.0189   1.0000   0.0355
  -9.750  -0.9681   0.02979   0.02240  -0.0167   1.0000   0.0369
  -9.500  -0.9551   0.02863   0.02110  -0.0143   1.0000   0.0388
  -9.250  -0.9424   0.02774   0.01999  -0.0117   1.0000   0.0409
  -9.000  -0.9271   0.02573   0.01794  -0.0100   1.0000   0.0438
  -8.750  -0.9134   0.02457   0.01679  -0.0078   1.0000   0.0468
  -8.500  -0.8997   0.02360   0.01568  -0.0053   1.0000   0.0507
  -8.250  -0.8899   0.02192   0.01404  -0.0024   1.0000   0.0559
  -8.000  -0.8783   0.02106   0.01310   0.0004   1.0000   0.0617
  -7.750  -0.8694   0.02006   0.01217   0.0037   1.0000   0.0680
  -7.500  -0.8563   0.01951   0.01156   0.0064   1.0000   0.0742
  -7.250  -0.8428   0.01912   0.01122   0.0089   1.0000   0.0808
  -7.000  -0.8283   0.01874   0.01079   0.0113   1.0000   0.0876
  -6.750  -0.8127   0.01847   0.01048   0.0135   1.0000   0.0951
  -6.500  -0.7985   0.01798   0.00999   0.0159   1.0000   0.1033
  -6.250  -0.7830   0.01758   0.00953   0.0182   1.0000   0.1139
  -6.000  -0.7697   0.01693   0.00891   0.0207   1.0000   0.1277
  -5.750  -0.7569   0.01622   0.00831   0.0233   1.0000   0.1434
  -5.500  -0.7419   0.01572   0.00787   0.0256   1.0000   0.1593
  -5.250  -0.7253   0.01533   0.00753   0.0276   1.0000   0.1747
  -5.000  -0.7084   0.01497   0.00721   0.0295   1.0000   0.1909
  -4.750  -0.6916   0.01460   0.00689   0.0314   1.0000   0.2088
  -4.500  -0.6756   0.01416   0.00657   0.0334   1.0000   0.2333
  -4.250  -0.6611   0.01363   0.00626   0.0356   1.0000   0.2738
  -4.000  -0.6486   0.01303   0.00606   0.0382   1.0000   0.3487
  -3.750  -0.6346   0.01263   0.00591   0.0406   1.0000   0.4144
  -3.500  -0.6208   0.01229   0.00583   0.0431   1.0000   0.4693
  -3.250  -0.5950   0.01212   0.00590   0.0432   0.9970   0.5282
  -3.000  -0.5590   0.01210   0.00607   0.0413   0.9911   0.5838
  -2.750  -0.5221   0.01214   0.00624   0.0393   0.9851   0.6293
  -2.500  -0.4880   0.01210   0.00629   0.0380   0.9784   0.6650
  -2.250  -0.4500   0.01211   0.00641   0.0359   0.9730   0.7030
  -2.000  -0.4174   0.01200   0.00641   0.0350   0.9654   0.7374
  -1.750  -0.3768   0.01197   0.00649   0.0326   0.9607   0.7683
  -1.500  -0.3398   0.01188   0.00651   0.0310   0.9529   0.7976
  -1.250  -0.2908   0.01184   0.00653   0.0269   0.9480   0.8229
  -1.000  -0.2465   0.01183   0.00658   0.0240   0.9406   0.8489
  -0.750  -0.1925   0.01192   0.00670   0.0192   0.9362   0.8702
  -0.500  -0.1375   0.01202   0.00681   0.0141   0.9335   0.8866
  -0.250  -0.0918   0.01214   0.00694   0.0109   0.9271   0.9001
   0.000  -0.0434   0.01213   0.00693   0.0070   0.9225   0.9106
   0.250   0.0162   0.01212   0.00692   0.0009   0.9202   0.9146
   0.500   0.0800   0.01212   0.00694  -0.0060   0.9181   0.9197
   0.750   0.1313   0.01212   0.00696  -0.0103   0.9085   0.9265
   1.000   0.1954   0.01200   0.00686  -0.0171   0.8994   0.9282
   1.250   0.2526   0.01194   0.00681  -0.0227   0.8864   0.9312
   1.500   0.2877   0.01195   0.00683  -0.0239   0.8676   0.9402
   1.750   0.3343   0.01191   0.00683  -0.0274   0.8475   0.9434
   2.000   0.3736   0.01187   0.00681  -0.0294   0.8211   0.9499
   2.250   0.4124   0.01178   0.00667  -0.0311   0.7835   0.9574
   2.500   0.4582   0.01178   0.00647  -0.0341   0.7328   0.9625
   2.750   0.4942   0.01199   0.00646  -0.0355   0.6868   0.9706
   3.000   0.5329   0.01210   0.00641  -0.0376   0.6347   0.9764
   3.250   0.5651   0.01224   0.00637  -0.0386   0.5716   0.9841
   3.500   0.5984   0.01248   0.00621  -0.0399   0.4792   0.9912
   3.750   0.6316   0.01286   0.00619  -0.0414   0.4018   0.9978
   4.000   0.6523   0.01321   0.00629  -0.0406   0.3479   1.0000
   4.250   0.6645   0.01356   0.00644  -0.0379   0.2998   1.0000
   4.500   0.6768   0.01398   0.00664  -0.0352   0.2531   1.0000
   4.750   0.6889   0.01449   0.00692  -0.0325   0.2110   1.0000
   5.000   0.7016   0.01505   0.00728  -0.0299   0.1737   1.0000
   5.250   0.7146   0.01563   0.00770  -0.0272   0.1480   1.0000
   5.500   0.7285   0.01617   0.00816  -0.0247   0.1301   1.0000
   5.750   0.7428   0.01672   0.00865  -0.0222   0.1176   1.0000
   6.000   0.7565   0.01736   0.00921  -0.0197   0.1081   1.0000
   6.250   0.7724   0.01783   0.00973  -0.0175   0.1003   1.0000
   6.500   0.7864   0.01859   0.01044  -0.0150   0.0937   1.0000
   6.750   0.8025   0.01907   0.01097  -0.0128   0.0871   1.0000
   7.000   0.8168   0.02003   0.01186  -0.0105   0.0816   1.0000
   7.250   0.8331   0.02051   0.01247  -0.0083   0.0765   1.0000
   7.500   0.8481   0.02124   0.01316  -0.0061   0.0716   1.0000
   7.750   0.8642   0.02225   0.01424  -0.0040   0.0672   1.0000
   8.000   0.8794   0.02286   0.01495  -0.0017   0.0629   1.0000
   8.250   0.8948   0.02399   0.01602   0.0002   0.0588   1.0000
   8.500   0.9095   0.02496   0.01718   0.0026   0.0551   1.0000
   8.750   0.9237   0.02580   0.01813   0.0050   0.0519   1.0000
   9.000   0.9378   0.02676   0.01905   0.0071   0.0489   1.0000
   9.250   0.9504   0.02838   0.02087   0.0096   0.0461   1.0000
   9.500   0.9618   0.02942   0.02212   0.0124   0.0438   1.0000
   9.750   0.9730   0.03057   0.02341   0.0150   0.0419   1.0000
  10.000   0.9846   0.03173   0.02460   0.0174   0.0402   1.0000
  10.250   0.9933   0.03440   0.02740   0.0197   0.0385   1.0000
  10.500   0.9951   0.03557   0.02889   0.0239   0.0374   1.0000
  10.750   0.9955   0.03718   0.03078   0.0279   0.0362   1.0000
  11.000   0.9947   0.03892   0.03276   0.0318   0.0352   1.0000
  11.250   0.9909   0.04078   0.03482   0.0360   0.0344   1.0000
  11.500   0.9849   0.04240   0.03659   0.0404   0.0338   1.0000
  11.750   0.9774   0.04425   0.03860   0.0445   0.0334   1.0000
  12.000   0.9663   0.04644   0.04098   0.0483   0.0331   1.0000
  12.250   0.9561   0.04869   0.04338   0.0514   0.0327   1.0000
  12.500   0.9399   0.05165   0.04654   0.0539   0.0325   1.0000
  12.750   0.9262   0.05457   0.04961   0.0555   0.0323   1.0000
  13.000   0.8550   0.06405   0.05969   0.0542   0.0338   1.0000
  13.250   0.7994   0.07476   0.07071   0.0479   0.0350   1.0000
  13.500   0.7366   0.09096   0.08710   0.0363   0.0367   1.0000
  13.750   0.6966   0.10453   0.10067   0.0287   0.0381   1.0000
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