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NASA NLF1015 (nlf1015-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NASA NLF1015 (nlf1015-il)
Reynolds number: 1,000,000
Max Cl/Cd: 167.74 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-nlf1015-il-1000000.txt
Download as CSV file: xf-nlf1015-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA  NLF1015                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.0924   0.08680   0.08494  -0.1339   0.9421   0.0141
 -11.000  -0.0796   0.08018   0.07829  -0.1415   0.9381   0.0152
 -10.750  -0.1041   0.05465   0.05257  -0.1672   0.9292   0.0164
 -10.500  -0.1027   0.04378   0.04131  -0.1876   0.9132   0.0164
 -10.250  -0.1089   0.03946   0.03668  -0.1929   0.8914   0.0164
 -10.000  -0.1267   0.03694   0.03392  -0.1920   0.8722   0.0164
  -9.750  -0.1440   0.03532   0.03212  -0.1888   0.8578   0.0164
  -9.500  -0.1532   0.03335   0.02991  -0.1866   0.8473   0.0164
  -8.750  -0.1803   0.01985   0.01507  -0.1784   0.8235   0.0127
  -8.500  -0.1615   0.01866   0.01369  -0.1778   0.8188   0.0127
  -8.250  -0.1410   0.01778   0.01269  -0.1772   0.8146   0.0126
  -8.000  -0.1216   0.01633   0.01108  -0.1765   0.8103   0.0128
  -7.750  -0.1005   0.01511   0.00973  -0.1760   0.8064   0.0130
  -7.500  -0.0784   0.01417   0.00870  -0.1755   0.8028   0.0131
  -7.250  -0.0560   0.01341   0.00790  -0.1750   0.7993   0.0133
  -7.000  -0.0327   0.01279   0.00722  -0.1747   0.7958   0.0136
  -6.750  -0.0082   0.01227   0.00663  -0.1746   0.7924   0.0139
  -6.500   0.0174   0.01185   0.00615  -0.1747   0.7891   0.0144
  -6.250   0.0421   0.01138   0.00565  -0.1746   0.7862   0.0147
  -6.000   0.0678   0.01098   0.00521  -0.1747   0.7834   0.0150
  -5.750   0.0943   0.01062   0.00479  -0.1748   0.7806   0.0154
  -5.500   0.1216   0.01030   0.00441  -0.1752   0.7779   0.0158
  -5.250   0.1503   0.01004   0.00408  -0.1758   0.7752   0.0161
  -5.000   0.1775   0.00978   0.00380  -0.1760   0.7730   0.0164
  -4.750   0.2050   0.00935   0.00332  -0.1764   0.7706   0.0178
  -4.500   0.2331   0.00911   0.00305  -0.1768   0.7681   0.0192
  -4.250   0.2616   0.00893   0.00283  -0.1773   0.7657   0.0206
  -4.000   0.2907   0.00876   0.00263  -0.1778   0.7634   0.0241
  -3.750   0.3211   0.00835   0.00242  -0.1790   0.7612   0.0772
  -3.500   0.3514   0.00792   0.00227  -0.1803   0.7592   0.1581
  -3.250   0.3815   0.00747   0.00214  -0.1815   0.7573   0.2533
  -3.000   0.4125   0.00703   0.00202  -0.1830   0.7553   0.3597
  -2.750   0.4445   0.00657   0.00192  -0.1846   0.7532   0.4830
  -2.500   0.4751   0.00642   0.00195  -0.1856   0.7512   0.5584
  -2.250   0.5049   0.00643   0.00197  -0.1862   0.7493   0.5874
  -2.000   0.5349   0.00648   0.00204  -0.1868   0.7474   0.6139
  -1.750   0.5653   0.00657   0.00210  -0.1876   0.7452   0.6255
  -1.500   0.5937   0.00660   0.00211  -0.1879   0.7436   0.6332
  -1.250   0.6222   0.00661   0.00215  -0.1882   0.7417   0.6403
  -1.000   0.6510   0.00666   0.00218  -0.1885   0.7398   0.6469
  -0.750   0.6799   0.00669   0.00220  -0.1890   0.7379   0.6522
  -0.500   0.7086   0.00673   0.00224  -0.1893   0.7359   0.6573
  -0.250   0.7378   0.00679   0.00228  -0.1898   0.7340   0.6627
   0.000   0.7676   0.00686   0.00233  -0.1904   0.7317   0.6675
   0.250   0.7963   0.00692   0.00240  -0.1908   0.7294   0.6722
   0.500   0.8235   0.00694   0.00244  -0.1908   0.7270   0.6768
   0.750   0.8512   0.00697   0.00247  -0.1910   0.7241   0.6808
   1.000   0.8788   0.00698   0.00250  -0.1911   0.7210   0.6848
   1.250   0.9071   0.00703   0.00254  -0.1914   0.7180   0.6887
   1.500   0.9358   0.00711   0.00261  -0.1918   0.7148   0.6924
   1.750   0.9620   0.00712   0.00265  -0.1916   0.7116   0.6954
   2.000   0.9889   0.00713   0.00268  -0.1916   0.7081   0.6980
   2.250   1.0160   0.00715   0.00272  -0.1916   0.7047   0.7007
   2.500   1.0449   0.00724   0.00279  -0.1921   0.7010   0.7033
   2.750   1.0702   0.00724   0.00286  -0.1917   0.6976   0.7062
   3.000   1.0959   0.00726   0.00291  -0.1914   0.6933   0.7090
   3.250   1.1222   0.00731   0.00295  -0.1913   0.6890   0.7117
   3.500   1.1487   0.00737   0.00302  -0.1912   0.6846   0.7145
   3.750   1.1733   0.00737   0.00311  -0.1907   0.6799   0.7175
   4.000   1.1982   0.00742   0.00317  -0.1903   0.6746   0.7206
   4.250   1.2230   0.00749   0.00326  -0.1898   0.6691   0.7238
   4.500   1.2466   0.00753   0.00335  -0.1891   0.6624   0.7269
   4.750   1.2688   0.00760   0.00343  -0.1881   0.6541   0.7301
   5.000   1.2866   0.00767   0.00351  -0.1861   0.6407   0.7335
   5.250   1.3023   0.00778   0.00362  -0.1837   0.6242   0.7374
   5.500   1.3149   0.00801   0.00379  -0.1806   0.6005   0.7415
   5.750   1.3183   0.00853   0.00413  -0.1757   0.5574   0.7456
   6.000   1.3145   0.00939   0.00473  -0.1696   0.5016   0.7500
   6.250   1.3136   0.01029   0.00539  -0.1642   0.4529   0.7547
   6.500   1.3167   0.01114   0.00604  -0.1598   0.4110   0.7593
   6.750   1.3193   0.01205   0.00677  -0.1555   0.3700   0.7642
   7.250   1.3236   0.01410   0.00845  -0.1471   0.2896   0.7751
   7.500   1.3243   0.01529   0.00946  -0.1429   0.2479   0.7809
   7.750   1.3265   0.01650   0.01049  -0.1392   0.2113   0.7874
   8.000   1.3315   0.01764   0.01150  -0.1360   0.1799   0.7936
   8.250   1.3363   0.01886   0.01258  -0.1329   0.1493   0.8005
   8.500   1.3406   0.02018   0.01375  -0.1299   0.1186   0.8075
   8.750   1.3442   0.02159   0.01503  -0.1269   0.0892   0.8153
   9.000   1.3466   0.02317   0.01644  -0.1239   0.0582   0.8233
   9.250   1.3478   0.02491   0.01802  -0.1209   0.0298   0.8324
   9.500   1.3507   0.02659   0.01962  -0.1181   0.0123   0.8421
   9.750   1.3633   0.02761   0.02070  -0.1166   0.0104   0.8535
  10.000   1.3753   0.02868   0.02183  -0.1150   0.0094   0.8670
  10.250   1.3858   0.02983   0.02310  -0.1132   0.0086   0.8838
  10.500   1.3966   0.03078   0.02416  -0.1114   0.0083   0.9110
  10.750   1.4033   0.03165   0.02517  -0.1088   0.0080   1.0000
  11.000   1.4158   0.03288   0.02645  -0.1076   0.0076   1.0000
  11.250   1.4278   0.03416   0.02778  -0.1065   0.0073   1.0000
  11.500   1.4383   0.03561   0.02927  -0.1052   0.0070   1.0000
  11.750   1.4478   0.03715   0.03087  -0.1038   0.0068   1.0000
  12.000   1.4553   0.03891   0.03271  -0.1024   0.0066   1.0000
  12.250   1.4601   0.04098   0.03487  -0.1008   0.0064   1.0000
  12.500   1.4647   0.04310   0.03708  -0.0993   0.0062   1.0000
  12.750   1.4737   0.04482   0.03887  -0.0982   0.0062   1.0000
  13.000   1.4819   0.04666   0.04077  -0.0971   0.0061   1.0000
  13.250   1.4892   0.04862   0.04280  -0.0961   0.0060   1.0000
  13.500   1.4957   0.05070   0.04496  -0.0951   0.0059   1.0000
  13.750   1.5014   0.05293   0.04727  -0.0941   0.0059   1.0000
  14.000   1.5068   0.05521   0.04964  -0.0932   0.0058   1.0000
  14.250   1.5107   0.05772   0.05223  -0.0923   0.0057   1.0000
  14.500   1.5149   0.06023   0.05482  -0.0915   0.0056   1.0000
  14.750   1.5184   0.06288   0.05756  -0.0908   0.0055   1.0000
  15.000   1.5212   0.06570   0.06046  -0.0902   0.0054   1.0000
  15.250   1.5239   0.06856   0.06341  -0.0897   0.0053   1.0000
  15.500   1.5257   0.07157   0.06651  -0.0893   0.0053   1.0000
  15.750   1.5268   0.07475   0.06978  -0.0890   0.0052   1.0000
  16.000   1.5277   0.07804   0.07316  -0.0888   0.0051   1.0000
  16.250   1.5283   0.08141   0.07662  -0.0887   0.0051   1.0000
  16.500   1.5281   0.08496   0.08027  -0.0888   0.0050   1.0000
  16.750   1.5274   0.08862   0.08404  -0.0890   0.0049   1.0000
  17.000   1.5262   0.09241   0.08792  -0.0893   0.0049   1.0000
  17.250   1.5248   0.09629   0.09189  -0.0898   0.0048   1.0000
  17.500   1.5229   0.10029   0.09598  -0.0905   0.0048   1.0000
  17.750   1.5207   0.10439   0.10018  -0.0913   0.0047   1.0000
  18.000   1.5178   0.10860   0.10449  -0.0923   0.0046   1.0000
  18.250   1.5133   0.11303   0.10902  -0.0933   0.0046   1.0000
  18.500   1.5082   0.11755   0.11366  -0.0944   0.0045   1.0000
  18.750   1.5029   0.12215   0.11838  -0.0957   0.0044   1.0000
  19.000   1.4971   0.12693   0.12330  -0.0973   0.0044   1.0000
  19.250   1.4926   0.13162   0.12812  -0.0993   0.0044   1.0000
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