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NLF(1)-0115 (nlf0115-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NLF(1)-0115 (nlf0115-il)
Reynolds number: 50,000
Max Cl/Cd: 26.82 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-nlf0115-il-50000-n5.txt
Download as CSV file: xf-nlf0115-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NLF(1)-0115                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.4212   0.11885   0.11126  -0.0512   1.0000   0.0584
 -11.750  -0.4198   0.11505   0.10751  -0.0517   1.0000   0.0580
 -11.500  -0.4187   0.11136   0.10386  -0.0521   1.0000   0.0573
 -11.250  -0.4201   0.10735   0.09991  -0.0529   1.0000   0.0564
 -11.000  -0.4259   0.10263   0.09525  -0.0545   1.0000   0.0557
 -10.750  -0.4339   0.09750   0.09018  -0.0565   1.0000   0.0548
 -10.500  -0.4479   0.09196   0.08471  -0.0588   1.0000   0.0536
 -10.250  -0.4677   0.08670   0.07949  -0.0606   1.0000   0.0526
 -10.000  -0.4938   0.08192   0.07472  -0.0613   1.0000   0.0517
  -9.750  -0.5265   0.07787   0.07064  -0.0604   1.0000   0.0506
  -9.250  -0.6238   0.07315   0.06558  -0.0497   1.0000   0.0481
  -9.000  -0.6394   0.07094   0.06331  -0.0459   1.0000   0.0480
  -8.750  -0.6564   0.06880   0.06107  -0.0418   1.0000   0.0480
  -8.500  -0.6685   0.06672   0.05891  -0.0379   1.0000   0.0479
  -8.250  -0.6807   0.06461   0.05666  -0.0340   1.0000   0.0478
  -8.000  -0.6882   0.06234   0.05422  -0.0307   0.9995   0.0477
  -7.750  -0.6713   0.05853   0.05005  -0.0322   0.9914   0.0476
  -7.500  -0.6518   0.05507   0.04620  -0.0335   0.9839   0.0474
  -7.250  -0.6329   0.05192   0.04263  -0.0341   0.9755   0.0474
  -7.000  -0.6118   0.04900   0.03928  -0.0345   0.9680   0.0475
  -6.750  -0.5874   0.04634   0.03616  -0.0351   0.9612   0.0477
  -6.250  -0.5360   0.04181   0.03110  -0.0361   0.9480   0.0495
  -6.000  -0.5083   0.04022   0.02938  -0.0368   0.9420   0.0517
  -5.750  -0.4803   0.03871   0.02763  -0.0372   0.9355   0.0542
  -5.500  -0.4435   0.03716   0.02581  -0.0385   0.9315   0.0563
  -5.250  -0.4104   0.03599   0.02442  -0.0386   0.9263   0.0582
  -5.000  -0.3743   0.03497   0.02340  -0.0392   0.9221   0.0607
  -4.750  -0.3407   0.03414   0.02252  -0.0401   0.9179   0.0656
  -4.500  -0.3172   0.03348   0.02172  -0.0392   0.9116   0.0716
  -4.250  -0.2972   0.03263   0.02092  -0.0384   0.9050   0.0782
  -4.000  -0.2763   0.03173   0.01997  -0.0377   0.8995   0.0880
  -3.750  -0.2659   0.03095   0.01924  -0.0354   0.8918   0.1028
  -3.500  -0.2499   0.02947   0.01815  -0.0346   0.8868   0.1497
  -3.250  -0.2667   0.02820   0.01979  -0.0248   0.8788   0.5885
  -3.000  -0.2605   0.02941   0.02073  -0.0188   0.8725   0.7129
  -2.750  -0.2404   0.03177   0.02301  -0.0112   0.8684   0.7822
  -2.500  -0.1482   0.03431   0.02511  -0.0155   0.8717   0.8433
  -2.250  -0.1474   0.03408   0.02474  -0.0117   0.8636   0.8492
  -2.000  -0.1178   0.03387   0.02428  -0.0128   0.8592   0.8521
  -1.750  -0.0859   0.03362   0.02381  -0.0144   0.8558   0.8552
  -1.500  -0.0899   0.03352   0.02362  -0.0098   0.8477   0.8606
  -1.250  -0.0717   0.03329   0.02324  -0.0090   0.8429   0.8643
  -1.000  -0.0373   0.03314   0.02289  -0.0109   0.8399   0.8663
  -0.750  -0.0333   0.03321   0.02289  -0.0078   0.8323   0.8702
  -0.500  -0.0128   0.03312   0.02268  -0.0074   0.8278   0.8735
  -0.250   0.0129   0.03297   0.02239  -0.0079   0.8243   0.8763
   0.000   0.0116   0.03306   0.02245  -0.0039   0.8166   0.8807
   0.250   0.0367   0.03310   0.02240  -0.0043   0.8122   0.8833
   0.500   0.0674   0.03308   0.02228  -0.0055   0.8088   0.8855
   0.750   0.0708   0.03326   0.02243  -0.0025   0.8015   0.8897
   1.000   0.0887   0.03329   0.02240  -0.0016   0.7962   0.8936
   1.250   0.1215   0.03332   0.02238  -0.0031   0.7928   0.8959
   1.500   0.1319   0.03366   0.02271  -0.0013   0.7852   0.8997
   1.750   0.1581   0.03378   0.02281  -0.0018   0.7799   0.9025
   2.000   0.1934   0.03379   0.02280  -0.0036   0.7763   0.9050
   2.250   0.1967   0.03418   0.02320  -0.0007   0.7669   0.9107
   2.500   0.2338   0.03426   0.02329  -0.0028   0.7621   0.9132
   2.750   0.2527   0.03462   0.02368  -0.0023   0.7535   0.9177
   3.000   0.2857   0.03465   0.02374  -0.0036   0.7470   0.9212
   3.250   0.3067   0.03484   0.02398  -0.0032   0.7376   0.9259
   3.500   0.3502   0.03456   0.02375  -0.0057   0.7301   0.9280
   3.750   0.3773   0.03460   0.02385  -0.0060   0.7178   0.9323
   4.000   0.4138   0.03424   0.02356  -0.0072   0.7071   0.9363
   4.250   0.4613   0.03341   0.02282  -0.0094   0.6976   0.9392
   4.500   0.4921   0.03323   0.02275  -0.0100   0.6840   0.9441
   4.750   0.5257   0.03293   0.02256  -0.0109   0.6706   0.9492
   5.000   0.5599   0.03247   0.02224  -0.0116   0.6573   0.9550
   5.250   0.5988   0.03189   0.02179  -0.0130   0.6431   0.9596
   5.500   0.6326   0.03138   0.02142  -0.0137   0.6269   0.9664
   5.750   0.6634   0.03093   0.02114  -0.0141   0.6083   0.9749
   6.000   0.6952   0.03034   0.02070  -0.0145   0.5880   0.9860
   6.250   0.6945   0.03041   0.02085  -0.0107   0.5657   1.0000
   6.500   0.6911   0.03046   0.02092  -0.0062   0.5424   1.0000
   6.750   0.6977   0.03054   0.02106  -0.0034   0.5130   1.0000
   7.000   0.7207   0.02997   0.02046  -0.0020   0.4793   1.0000
   7.250   0.7521   0.02912   0.01940  -0.0011   0.4363   1.0000
   7.500   0.7773   0.02898   0.01889   0.0001   0.3922   1.0000
   7.750   0.7933   0.02961   0.01917   0.0017   0.3573   1.0000
   8.000   0.8060   0.03056   0.01988   0.0032   0.3295   1.0000
   8.250   0.8194   0.03158   0.02069   0.0045   0.3074   1.0000
   8.500   0.8340   0.03263   0.02163   0.0057   0.2883   1.0000
   8.750   0.8499   0.03368   0.02260   0.0066   0.2716   1.0000
   9.000   0.8675   0.03470   0.02356   0.0073   0.2571   1.0000
   9.250   0.8871   0.03569   0.02449   0.0078   0.2442   1.0000
   9.500   0.9076   0.03668   0.02543   0.0083   0.2322   1.0000
   9.750   0.9275   0.03773   0.02659   0.0087   0.2208   1.0000
  10.000   0.9507   0.03875   0.02765   0.0088   0.2109   1.0000
  10.250   0.9758   0.03971   0.02858   0.0088   0.2014   1.0000
  10.500   0.9940   0.04097   0.03004   0.0093   0.1925   1.0000
  10.750   1.0203   0.04203   0.03107   0.0091   0.1847   1.0000
  11.000   1.0353   0.04348   0.03276   0.0098   0.1770   1.0000
  11.250   1.0596   0.04462   0.03385   0.0097   0.1702   1.0000
  11.500   1.0695   0.04638   0.03593   0.0109   0.1638   1.0000
  11.750   1.0883   0.04776   0.03738   0.0112   0.1581   1.0000
  12.000   1.0993   0.04958   0.03939   0.0121   0.1527   1.0000
  12.250   1.1050   0.05156   0.04161   0.0133   0.1476   1.0000
  12.500   1.1224   0.05304   0.04312   0.0137   0.1429   1.0000
  12.750   1.1251   0.05543   0.04576   0.0149   0.1390   1.0000
  13.000   1.1190   0.05827   0.04891   0.0163   0.1353   1.0000
  13.250   1.1201   0.06064   0.05148   0.0172   0.1315   1.0000
  13.500   1.1407   0.06192   0.05267   0.0174   0.1274   1.0000
  13.750   1.1192   0.06611   0.05726   0.0186   0.1255   1.0000
  14.000   1.0960   0.07088   0.06235   0.0191   0.1237   1.0000
  14.250   1.0678   0.07652   0.06829   0.0187   0.1222   1.0000
  14.500   1.0301   0.08384   0.07585   0.0171   0.1213   1.0000
  14.750   0.9557   0.09766   0.08988   0.0112   0.1218   1.0000
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