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NASA/LANGLEY NLF(1)-0215F AIRFOIL (nlf0215f-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NASA/LANGLEY NLF(1)-0215F AIRFOIL (nlf0215f-il)
Reynolds number: 100,000
Max Cl/Cd: 46.83 at α=10.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-nlf0215f-il-100000.txt
Download as CSV file: xf-nlf0215f-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA/LANGLEY NLF(1)-0215F AIRFOIL               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3375   0.12237   0.11781  -0.0490   1.0000   0.0934
 -10.000  -0.3661   0.12189   0.11751  -0.0478   1.0000   0.0937
  -9.750  -0.3941   0.12198   0.11776  -0.0445   1.0000   0.0938
  -9.500  -0.3829   0.11821   0.11403  -0.0395   1.0000   0.0952
  -9.250  -0.3484   0.11469   0.11046  -0.0391   0.9971   0.1001
  -9.000  -0.3388   0.11006   0.10584  -0.0476   0.9901   0.1071
  -8.750  -0.3652   0.10401   0.09984  -0.0658   0.9761   0.1089
  -8.500  -0.3002   0.10078   0.09656  -0.0563   0.9781   0.1160
  -8.250  -0.3072   0.09580   0.09160  -0.0673   0.9663   0.1235
  -8.000  -0.2859   0.09050   0.08630  -0.0708   0.9621   0.1278
  -7.750  -0.2651   0.08748   0.08326  -0.0720   0.9535   0.1338
  -7.500  -0.3124   0.08112   0.07683  -0.0875   0.9313   0.1401
  -7.250  -0.2630   0.07811   0.07392  -0.0827   0.9330   0.1467
  -7.000  -0.3055   0.07329   0.06873  -0.0958   0.9113   0.1567
  -6.750  -0.2597   0.06919   0.06491  -0.0924   0.9113   0.1628
  -6.000  -0.2305   0.05831   0.05372  -0.1019   0.8893   0.2093
  -5.750  -0.2244   0.05622   0.05161  -0.1010   0.8799   0.2260
  -5.500  -0.1740   0.04391   0.03731  -0.1141   0.8757   0.1076
  -5.250  -0.1604   0.03956   0.03218  -0.1118   0.8665   0.0780
  -5.000  -0.1250   0.03628   0.02860  -0.1140   0.8632   0.0748
  -4.750  -0.0826   0.03354   0.02539  -0.1168   0.8610   0.0739
  -4.500  -0.0366   0.03093   0.02231  -0.1197   0.8594   0.0714
  -4.250  -0.0324   0.03060   0.02182  -0.1158   0.8493   0.0709
  -4.000   0.0072   0.02897   0.01999  -0.1174   0.8466   0.0716
  -3.750   0.0481   0.02759   0.01853  -0.1192   0.8444   0.0745
  -3.500   0.0532   0.02780   0.01868  -0.1156   0.8363   0.0773
  -3.250   0.0801   0.02695   0.01790  -0.1153   0.8319   0.0828
  -3.000   0.1177   0.02596   0.01697  -0.1167   0.8293   0.0924
  -2.750   0.1562   0.02476   0.01596  -0.1185   0.8271   0.1216
  -2.500   0.1482   0.02357   0.01708  -0.1145   0.8183   0.5056
  -2.250   0.1433   0.02659   0.02031  -0.1030   0.8131   0.7261
  -2.000   0.1489   0.02778   0.02144  -0.0942   0.8104   0.7659
  -1.750   0.1219   0.02935   0.02305  -0.0866   0.7991   0.7747
  -1.500   0.1178   0.02997   0.02365  -0.0773   0.7956   0.8087
  -1.250   0.0968   0.03131   0.02501  -0.0696   0.7871   0.8247
  -1.000   0.0836   0.03180   0.02550  -0.0607   0.7820   0.8543
  -0.750   0.0753   0.03157   0.02524  -0.0513   0.7789   0.8926
  -0.500   0.0951   0.03123   0.02480  -0.0464   0.7761   0.9410
   0.000   0.1700   0.03242   0.02567  -0.0530   0.7664   0.9634
   0.250   0.2155   0.03236   0.02544  -0.0568   0.7637   0.9658
   0.500   0.2659   0.03209   0.02499  -0.0609   0.7618   0.9677
   0.750   0.2163   0.03411   0.02711  -0.0516   0.7519   0.9739
   1.000   0.2510   0.03433   0.02721  -0.0538   0.7483   0.9756
   1.250   0.2948   0.03426   0.02701  -0.0568   0.7458   0.9767
   1.500   0.2753   0.03597   0.02875  -0.0523   0.7375   0.9813
   1.750   0.2967   0.03644   0.02916  -0.0525   0.7328   0.9835
   2.000   0.3376   0.03649   0.02913  -0.0551   0.7298   0.9846
   2.250   0.3365   0.03802   0.03066  -0.0534   0.7224   0.9879
   2.500   0.3599   0.03866   0.03127  -0.0542   0.7167   0.9906
   2.750   0.4009   0.03868   0.03123  -0.0565   0.7134   0.9919
   3.000   0.3929   0.04032   0.03289  -0.0538   0.7048   0.9991
   3.250   0.4096   0.04076   0.03331  -0.0530   0.6994   1.0000
   3.500   0.4529   0.04058   0.03308  -0.0550   0.6962   1.0000
   3.750   0.4331   0.04256   0.03509  -0.0511   0.6856   1.0000
   4.000   0.4733   0.04260   0.03511  -0.0531   0.6812   1.0000
   4.250   0.4788   0.04413   0.03666  -0.0522   0.6722   1.0000
   4.500   0.5131   0.04443   0.03696  -0.0537   0.6662   1.0000
   4.750   0.5638   0.04402   0.03655  -0.0564   0.6632   1.0000
   5.000   0.5612   0.04605   0.03862  -0.0551   0.6508   1.0000
   5.250   0.6115   0.04554   0.03813  -0.0576   0.6474   1.0000
   5.500   0.6144   0.04744   0.04009  -0.0569   0.6350   1.0000
   5.750   0.6654   0.04672   0.03940  -0.0592   0.6314   1.0000
   6.000   0.6720   0.04849   0.04122  -0.0587   0.6188   1.0000
   6.250   0.7249   0.04741   0.04021  -0.0609   0.6153   1.0000
   6.500   0.7336   0.04908   0.04194  -0.0606   0.6024   1.0000
   6.750   0.7873   0.04771   0.04065  -0.0626   0.5992   1.0000
   7.000   0.7980   0.04922   0.04222  -0.0623   0.5860   1.0000
   7.250   0.8560   0.04716   0.04028  -0.0642   0.5833   1.0000
   7.500   0.9216   0.04412   0.03737  -0.0663   0.5820   1.0000
   7.750   0.9966   0.04009   0.03348  -0.0689   0.5817   1.0000
   8.000   1.0037   0.04138   0.03486  -0.0677   0.5674   1.0000
   8.250   1.0901   0.03656   0.03021  -0.0715   0.5668   1.0000
   8.500   1.1047   0.03692   0.03069  -0.0703   0.5535   1.0000
   8.750   1.2158   0.03101   0.02493  -0.0776   0.5503   1.0000
   9.000   1.2368   0.03055   0.02461  -0.0764   0.5362   1.0000
   9.250   1.2664   0.02957   0.02375  -0.0760   0.5212   1.0000
   9.500   1.2983   0.02842   0.02269  -0.0759   0.5043   1.0000
   9.750   1.3111   0.02835   0.02273  -0.0738   0.4841   1.0000
  10.000   1.3248   0.02834   0.02278  -0.0719   0.4597   1.0000
  10.250   1.3376   0.02856   0.02298  -0.0701   0.4299   1.0000
  10.500   1.3491   0.02911   0.02334  -0.0682   0.3948   1.0000
  10.750   1.3507   0.03060   0.02464  -0.0659   0.3588   1.0000
  11.000   1.3511   0.03245   0.02625  -0.0637   0.3246   1.0000
  11.250   1.3505   0.03459   0.02818  -0.0618   0.2942   1.0000
  11.500   1.3513   0.03683   0.03019  -0.0602   0.2676   1.0000
  11.750   1.3525   0.03916   0.03236  -0.0589   0.2440   1.0000
  12.000   1.3568   0.04139   0.03440  -0.0579   0.2232   1.0000
  12.250   1.3617   0.04367   0.03662  -0.0570   0.2047   1.0000
  12.500   1.3685   0.04587   0.03875  -0.0564   0.1886   1.0000
  12.750   1.3771   0.04800   0.04084  -0.0558   0.1744   1.0000
  13.000   1.3881   0.05004   0.04281  -0.0554   0.1617   1.0000
  13.250   1.4026   0.05189   0.04455  -0.0551   0.1500   1.0000
  13.500   1.4109   0.05414   0.04690  -0.0548   0.1404   1.0000
  13.750   1.4240   0.05627   0.04911  -0.0545   0.1315   1.0000
  14.000   1.4457   0.05790   0.05060  -0.0545   0.1223   1.0000
  14.250   1.4488   0.06065   0.05365  -0.0541   0.1163   1.0000
  14.500   1.4719   0.06236   0.05523  -0.0543   0.1085   1.0000
  14.750   1.4708   0.06547   0.05867  -0.0539   0.1038   1.0000
  15.000   1.4983   0.06708   0.06008  -0.0542   0.0964   1.0000
  15.250   1.4894   0.07073   0.06413  -0.0537   0.0933   1.0000
  15.500   1.4871   0.07406   0.06770  -0.0536   0.0893   1.0000
  15.750   1.5059   0.07621   0.06974  -0.0538   0.0835   1.0000
  16.000   1.4918   0.08059   0.07452  -0.0538   0.0811   1.0000
  16.250   1.4828   0.08473   0.07893  -0.0542   0.0781   1.0000
  16.500   1.5055   0.08646   0.08042  -0.0544   0.0724   1.0000
  16.750   1.4845   0.09178   0.08615  -0.0552   0.0712   1.0000
  17.000   1.4644   0.09749   0.09222  -0.0565   0.0698   1.0000
  17.250   1.4457   0.10339   0.09844  -0.0582   0.0683   1.0000
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