Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

N-13 (n13-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: N-13 (n13-il)
Reynolds number: 1,000,000
Max Cl/Cd: 73.06 at α=9°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n13-il-1000000.txt
Download as CSV file: xf-n13-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -17.750  -1.0399   0.10012   0.09730  -0.0234   1.0000   0.0079
 -17.500  -1.0572   0.09302   0.09010  -0.0270   1.0000   0.0079
 -17.250  -1.0881   0.08393   0.08086  -0.0315   1.0000   0.0078
 -17.000  -1.1011   0.07782   0.07462  -0.0347   1.0000   0.0079
 -16.750  -1.1131   0.07210   0.06879  -0.0377   1.0000   0.0079
 -16.500  -1.1302   0.06587   0.06243  -0.0407   1.0000   0.0079
 -16.250  -1.1408   0.06083   0.05727  -0.0431   1.0000   0.0079
 -16.000  -1.1505   0.05613   0.05244  -0.0451   1.0000   0.0079
 -15.750  -1.1618   0.05153   0.04771  -0.0468   1.0000   0.0079
 -15.500  -1.1799   0.04639   0.04240  -0.0482   1.0000   0.0081
 -15.250  -1.1800   0.04362   0.03954  -0.0487   1.0000   0.0080
 -15.000  -1.1959   0.03937   0.03512  -0.0489   1.0000   0.0082
 -14.750  -1.2098   0.03568   0.03129  -0.0484   1.0000   0.0084
 -14.500  -1.2141   0.03317   0.02867  -0.0473   1.0000   0.0084
 -14.250  -1.2157   0.03111   0.02652  -0.0460   1.0000   0.0086
 -14.000  -1.2144   0.02944   0.02477  -0.0443   1.0000   0.0088
 -13.750  -1.2107   0.02806   0.02331  -0.0424   1.0000   0.0089
 -13.500  -1.2074   0.02676   0.02193  -0.0402   1.0000   0.0091
 -13.250  -1.2040   0.02555   0.02063  -0.0377   1.0000   0.0091
 -13.000  -1.1970   0.02463   0.01965  -0.0353   1.0000   0.0094
 -12.750  -1.1913   0.02369   0.01863  -0.0326   1.0000   0.0097
 -12.500  -1.1850   0.02286   0.01772  -0.0297   1.0000   0.0099
 -12.250  -1.1777   0.02215   0.01694  -0.0267   1.0000   0.0101
 -12.000  -1.1722   0.02144   0.01615  -0.0233   1.0000   0.0102
 -11.750  -1.1640   0.02093   0.01558  -0.0200   1.0000   0.0104
 -11.500  -1.1588   0.02038   0.01495  -0.0161   1.0000   0.0105
 -11.250  -1.1579   0.01947   0.01396  -0.0116   1.0000   0.0108
 -11.000  -1.1524   0.01854   0.01295  -0.0078   1.0000   0.0113
 -10.750  -1.1405   0.01795   0.01233  -0.0052   1.0000   0.0117
 -10.500  -1.1277   0.01740   0.01172  -0.0026   1.0000   0.0121
 -10.250  -1.1138   0.01691   0.01120  -0.0001   1.0000   0.0126
 -10.000  -1.1002   0.01646   0.01069   0.0024   1.0000   0.0131
  -9.750  -1.0876   0.01607   0.01025   0.0052   1.0000   0.0134
  -9.500  -1.0629   0.01539   0.00950   0.0053   0.9989   0.0142
  -9.250  -1.0335   0.01476   0.00884   0.0044   0.9972   0.0152
  -9.000  -1.0031   0.01427   0.00832   0.0034   0.9955   0.0162
  -8.750  -0.9719   0.01387   0.00786   0.0023   0.9942   0.0173
  -8.500  -0.9449   0.01327   0.00728   0.0020   0.9919   0.0205
  -8.250  -0.9162   0.01279   0.00685   0.0015   0.9894   0.0256
  -8.000  -0.8855   0.01245   0.00658   0.0005   0.9874   0.0328
  -7.750  -0.8543   0.01214   0.00630  -0.0005   0.9857   0.0379
  -7.500  -0.8218   0.01196   0.00611  -0.0017   0.9846   0.0408
  -7.250  -0.7939   0.01171   0.00583  -0.0020   0.9818   0.0431
  -7.000  -0.7677   0.01131   0.00544  -0.0018   0.9778   0.0465
  -6.750  -0.7377   0.01102   0.00512  -0.0025   0.9754   0.0489
  -6.500  -0.7067   0.01077   0.00484  -0.0034   0.9737   0.0507
  -6.250  -0.6750   0.01053   0.00458  -0.0044   0.9724   0.0522
  -6.000  -0.6528   0.01022   0.00425  -0.0033   0.9666   0.0558
  -5.750  -0.6243   0.00987   0.00393  -0.0036   0.9634   0.0608
  -5.500  -0.5951   0.00946   0.00366  -0.0041   0.9610   0.0806
  -5.250  -0.5646   0.00924   0.00350  -0.0048   0.9592   0.0981
  -5.000  -0.5392   0.00901   0.00330  -0.0043   0.9540   0.1064
  -4.750  -0.5082   0.00884   0.00313  -0.0050   0.9511   0.1116
  -4.500  -0.4748   0.00865   0.00293  -0.0063   0.9491   0.1164
  -4.250  -0.4402   0.00842   0.00273  -0.0079   0.9472   0.1225
  -4.000  -0.4067   0.00825   0.00257  -0.0092   0.9440   0.1263
  -3.750  -0.3697   0.00805   0.00239  -0.0113   0.9401   0.1333
  -3.500  -0.3272   0.00778   0.00219  -0.0148   0.9360   0.1487
  -3.250  -0.2884   0.00737   0.00198  -0.0175   0.9310   0.1985
  -3.000  -0.2552   0.00703   0.00180  -0.0189   0.9243   0.2437
  -2.750  -0.2230   0.00654   0.00161  -0.0203   0.9181   0.3256
  -2.500  -0.1989   0.00629   0.00153  -0.0195   0.9103   0.3767
  -2.250  -0.1693   0.00608   0.00145  -0.0201   0.9033   0.4212
  -2.000  -0.1483   0.00589   0.00140  -0.0186   0.8952   0.4611
  -1.750  -0.1230   0.00572   0.00135  -0.0180   0.8874   0.5008
  -1.500  -0.1017   0.00558   0.00132  -0.0165   0.8787   0.5341
  -1.250  -0.0782   0.00546   0.00129  -0.0154   0.8705   0.5678
  -1.000  -0.0560   0.00534   0.00126  -0.0141   0.8606   0.5988
  -0.750  -0.0346   0.00522   0.00123  -0.0125   0.8476   0.6277
  -0.500  -0.0134   0.00513   0.00118  -0.0109   0.8282   0.6524
  -0.250   0.0067   0.00510   0.00110  -0.0090   0.7880   0.6707
   0.000   0.0258   0.00518   0.00105  -0.0068   0.7450   0.6863
   0.250   0.0471   0.00525   0.00106  -0.0053   0.7209   0.7026
   0.500   0.0699   0.00527   0.00108  -0.0041   0.7042   0.7193
   0.750   0.0929   0.00529   0.00110  -0.0029   0.6889   0.7366
   1.000   0.1158   0.00529   0.00113  -0.0017   0.6742   0.7555
   1.250   0.1383   0.00526   0.00116  -0.0004   0.6606   0.7780
   1.500   0.1605   0.00525   0.00119   0.0010   0.6425   0.8025
   1.750   0.1821   0.00524   0.00124   0.0025   0.6173   0.8332
   2.000   0.2048   0.00530   0.00132   0.0038   0.5859   0.8647
   2.250   0.2289   0.00547   0.00143   0.0048   0.5416   0.8902
   2.500   0.2502   0.00579   0.00157   0.0063   0.4771   0.9103
   2.750   0.2729   0.00610   0.00171   0.0074   0.4305   0.9234
   3.000   0.3007   0.00640   0.00188   0.0074   0.3912   0.9320
   3.250   0.3237   0.00664   0.00202   0.0085   0.3590   0.9413
   3.500   0.3546   0.00694   0.00219   0.0078   0.3223   0.9465
   3.750   0.3755   0.00719   0.00233   0.0093   0.2913   0.9545
   4.000   0.4101   0.00757   0.00256   0.0077   0.2517   0.9578
   4.250   0.4451   0.00799   0.00281   0.0060   0.2121   0.9606
   4.500   0.4849   0.00845   0.00313   0.0033   0.1802   0.9650
   4.750   0.5121   0.00878   0.00338   0.0034   0.1564   0.9701
   5.000   0.5484   0.00919   0.00364   0.0013   0.1267   0.9712
   5.250   0.5829   0.00956   0.00390  -0.0003   0.1019   0.9725
   5.500   0.6159   0.00994   0.00417  -0.0017   0.0839   0.9740
   5.750   0.6482   0.01026   0.00443  -0.0028   0.0729   0.9758
   6.000   0.6789   0.01052   0.00468  -0.0035   0.0657   0.9782
   6.250   0.7022   0.01087   0.00499  -0.0026   0.0584   0.9821
   6.500   0.7348   0.01107   0.00521  -0.0038   0.0547   0.9834
   6.750   0.7679   0.01140   0.00549  -0.0052   0.0493   0.9844
   7.000   0.8011   0.01165   0.00576  -0.0066   0.0459   0.9856
   7.250   0.8333   0.01191   0.00602  -0.0077   0.0427   0.9871
   7.500   0.8634   0.01230   0.00639  -0.0085   0.0385   0.9889
   7.750   0.8941   0.01251   0.00663  -0.0093   0.0363   0.9907
   8.000   0.9218   0.01284   0.00693  -0.0095   0.0330   0.9927
   8.250   0.9503   0.01319   0.00730  -0.0099   0.0302   0.9943
   8.500   0.9816   0.01349   0.00758  -0.0110   0.0270   0.9954
   8.750   1.0115   0.01390   0.00800  -0.0118   0.0242   0.9968
   9.000   1.0411   0.01425   0.00836  -0.0125   0.0219   0.9982
   9.250   1.0696   0.01476   0.00889  -0.0131   0.0196   0.9996
   9.500   1.0917   0.01510   0.00925  -0.0122   0.0183   1.0000
   9.750   1.1061   0.01549   0.00966  -0.0098   0.0172   1.0000
  10.000   1.1160   0.01614   0.01035  -0.0065   0.0159   1.0000
  10.250   1.1305   0.01646   0.01073  -0.0041   0.0155   1.0000
  10.500   1.1429   0.01688   0.01120  -0.0012   0.0149   1.0000
  10.750   1.1551   0.01727   0.01163   0.0016   0.0143   1.0000
  11.000   1.1649   0.01774   0.01215   0.0048   0.0138   1.0000
  11.250   1.1718   0.01832   0.01277   0.0085   0.0132   1.0000
  11.500   1.1702   0.01916   0.01368   0.0138   0.0125   1.0000
  11.750   1.1730   0.01953   0.01411   0.0183   0.0124   1.0000
  12.000   1.1773   0.01994   0.01459   0.0225   0.0122   1.0000
  12.250   1.1825   0.02047   0.01520   0.0263   0.0119   1.0000
  12.500   1.1914   0.02095   0.01573   0.0294   0.0115   1.0000
  12.750   1.1983   0.02161   0.01645   0.0325   0.0113   1.0000
  13.000   1.2053   0.02235   0.01726   0.0355   0.0110   1.0000
  13.250   1.2134   0.02310   0.01807   0.0380   0.0107   1.0000
  13.500   1.2186   0.02408   0.01911   0.0407   0.0103   1.0000
  13.750   1.2214   0.02528   0.02039   0.0434   0.0101   1.0000
  14.000   1.2113   0.02742   0.02266   0.0469   0.0097   1.0000
  14.250   1.2085   0.02925   0.02461   0.0493   0.0096   1.0000
  14.500   1.2163   0.03041   0.02586   0.0506   0.0096   1.0000
  14.750   1.2208   0.03192   0.02747   0.0518   0.0094   1.0000
  15.000   1.2236   0.03369   0.02934   0.0528   0.0093   1.0000
  15.250   1.2207   0.03614   0.03191   0.0536   0.0092   1.0000
  15.500   1.2217   0.03842   0.03430   0.0538   0.0091   1.0000
  15.750   1.2175   0.04142   0.03742   0.0536   0.0089   1.0000
  16.000   1.2168   0.04424   0.04034   0.0530   0.0087   1.0000
  16.250   1.2074   0.04828   0.04451   0.0518   0.0086   1.0000
  16.500   1.1947   0.05307   0.04945   0.0499   0.0086   1.0000
  16.750   1.1798   0.05857   0.05509   0.0472   0.0086   1.0000
  17.000   1.1701   0.06368   0.06031   0.0445   0.0084   1.0000
  17.250   1.1476   0.07101   0.06780   0.0405   0.0086   1.0000
  17.500   1.1286   0.07791   0.07483   0.0368   0.0086   1.0000
  17.750   1.1022   0.08629   0.08334   0.0324   0.0084   1.0000
  18.000   1.0792   0.09418   0.09136   0.0282   0.0084   1.0000
  18.250   1.0437   0.10434   0.10167   0.0230   0.0086   1.0000
  18.500   1.0194   0.11287   0.11031   0.0185   0.0086   1.0000
<< Back to N-13 (n13-il)

Polar data table (+)

Polar graphs


<< Back to N-13 (n13-il)