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NASA/LANGLEY NLF(1)-0416 AIRFOIL (nlf416-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NASA/LANGLEY NLF(1)-0416 AIRFOIL (nlf416-il)
Reynolds number: 200,000
Max Cl/Cd: 65.32 at α=9°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-nlf416-il-200000.txt
Download as CSV file: xf-nlf416-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA/LANGLEY NLF(1)-0416 AIRFOIL                
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.3964   0.11265   0.10901  -0.0384   1.0000   0.0690
 -11.250  -0.3998   0.07705   0.07371  -0.0564   1.0000   0.0479
 -11.000  -0.4788   0.05968   0.05612  -0.0653   1.0000   0.0418
 -10.750  -0.4390   0.09342   0.08996  -0.0486   1.0000   0.0763
 -10.500  -0.4373   0.09020   0.08677  -0.0486   1.0000   0.0772
 -10.250  -0.4434   0.08555   0.08216  -0.0502   1.0000   0.0783
 -10.000  -0.4680   0.07756   0.07422  -0.0551   1.0000   0.0798
  -9.750  -0.7563   0.04691   0.04149  -0.0546   1.0000   0.0329
  -9.500  -0.7479   0.04335   0.03791  -0.0531   1.0000   0.0322
  -9.250  -0.7463   0.04041   0.03481  -0.0511   1.0000   0.0317
  -9.000  -0.7426   0.03776   0.03194  -0.0491   1.0000   0.0312
  -8.750  -0.7363   0.03530   0.02922  -0.0472   1.0000   0.0307
  -8.500  -0.7273   0.03302   0.02667  -0.0454   1.0000   0.0303
  -8.250  -0.7024   0.03068   0.02401  -0.0462   0.9977   0.0303
  -8.000  -0.6629   0.02854   0.02159  -0.0491   0.9933   0.0306
  -7.750  -0.6242   0.02678   0.01962  -0.0516   0.9877   0.0313
  -7.500  -0.5825   0.02531   0.01798  -0.0544   0.9833   0.0323
  -7.250  -0.5473   0.02378   0.01647  -0.0562   0.9763   0.0340
  -7.000  -0.5055   0.02267   0.01539  -0.0594   0.9714   0.0364
  -6.750  -0.4695   0.02160   0.01425  -0.0611   0.9620   0.0388
  -6.500  -0.4346   0.02009   0.01287  -0.0633   0.9528   0.0420
  -6.250  -0.3933   0.01872   0.01150  -0.0667   0.9458   0.0477
  -6.000  -0.3579   0.01739   0.01026  -0.0690   0.9342   0.0609
  -5.750  -0.3217   0.01522   0.00867  -0.0724   0.9233   0.1424
  -5.500  -0.2768   0.01369   0.00768  -0.0773   0.9154   0.2470
  -5.250  -0.2332   0.01250   0.00693  -0.0815   0.9014   0.3494
  -5.000  -0.1878   0.01155   0.00644  -0.0856   0.8854   0.4563
  -4.750  -0.1446   0.01143   0.00667  -0.0878   0.8658   0.5398
  -4.500  -0.1061   0.01194   0.00716  -0.0886   0.8393   0.5816
  -4.250  -0.0696   0.01246   0.00744  -0.0894   0.8123   0.6054
  -4.000  -0.0389   0.01305   0.00781  -0.0890   0.7854   0.6214
  -3.750  -0.0103   0.01363   0.00815  -0.0883   0.7618   0.6349
  -3.500   0.0164   0.01419   0.00851  -0.0873   0.7406   0.6465
  -3.250   0.0410   0.01479   0.00897  -0.0856   0.7227   0.6531
  -3.000   0.0686   0.01515   0.00913  -0.0853   0.7072   0.6651
  -2.750   0.0920   0.01572   0.00958  -0.0832   0.6942   0.6694
  -2.500   0.1172   0.01610   0.00985  -0.0820   0.6812   0.6778
  -2.250   0.1420   0.01641   0.01007  -0.0809   0.6697   0.6849
  -2.000   0.1665   0.01681   0.01034  -0.0794   0.6605   0.6907
  -1.750   0.1932   0.01692   0.01036  -0.0792   0.6504   0.6999
  -1.500   0.2167   0.01725   0.01059  -0.0774   0.6425   0.7044
  -1.250   0.2455   0.01729   0.01054  -0.0780   0.6335   0.7148
  -1.000   0.2680   0.01755   0.01072  -0.0760   0.6269   0.7183
  -0.750   0.2920   0.01769   0.01085  -0.0749   0.6192   0.7244
  -0.500   0.3204   0.01771   0.01076  -0.0753   0.6123   0.7322
  -0.250   0.3433   0.01786   0.01087  -0.0737   0.6062   0.7364
   0.000   0.3699   0.01791   0.01089  -0.0736   0.5994   0.7431
   0.250   0.3974   0.01793   0.01082  -0.0736   0.5937   0.7489
   0.500   0.4205   0.01801   0.01090  -0.0723   0.5879   0.7531
   0.750   0.4479   0.01804   0.01090  -0.0724   0.5816   0.7592
   1.000   0.4769   0.01806   0.01082  -0.0729   0.5764   0.7644
   1.250   0.4996   0.01810   0.01088  -0.0716   0.5708   0.7682
   1.500   0.5257   0.01812   0.01090  -0.0714   0.5649   0.7728
   1.750   0.5591   0.01819   0.01087  -0.0731   0.5596   0.7781
   2.000   0.5826   0.01817   0.01088  -0.0722   0.5542   0.7811
   2.250   0.6070   0.01817   0.01091  -0.0715   0.5484   0.7843
   2.500   0.6350   0.01822   0.01089  -0.0716   0.5431   0.7878
   2.750   0.6643   0.01830   0.01098  -0.0724   0.5376   0.7914
   3.000   0.6957   0.01835   0.01103  -0.0737   0.5312   0.7948
   3.250   0.7208   0.01833   0.01098  -0.0731   0.5261   0.7970
   3.500   0.7460   0.01838   0.01108  -0.0727   0.5204   0.7995
   3.750   0.7723   0.01841   0.01115  -0.0726   0.5141   0.8021
   4.000   0.8021   0.01848   0.01115  -0.0732   0.5086   0.8047
   4.250   0.8307   0.01858   0.01132  -0.0738   0.5023   0.8073
   4.500   0.8611   0.01864   0.01139  -0.0748   0.4955   0.8095
   4.750   0.8910   0.01874   0.01140  -0.0754   0.4900   0.8114
   5.000   0.9137   0.01872   0.01155  -0.0745   0.4828   0.8132
   5.250   0.9411   0.01874   0.01155  -0.0746   0.4762   0.8148
   5.500   0.9676   0.01883   0.01168  -0.0746   0.4695   0.8167
   5.750   0.9940   0.01885   0.01176  -0.0745   0.4617   0.8187
   6.000   1.0233   0.01894   0.01182  -0.0751   0.4550   0.8201
   6.250   1.0491   0.01898   0.01197  -0.0751   0.4464   0.8219
   6.500   1.0792   0.01908   0.01200  -0.0758   0.4394   0.8237
   6.750   1.1046   0.01912   0.01219  -0.0757   0.4299   0.8251
   7.000   1.1334   0.01920   0.01223  -0.0762   0.4221   0.8262
   7.250   1.1560   0.01919   0.01236  -0.0755   0.4122   0.8274
   7.500   1.1800   0.01924   0.01244  -0.0749   0.4032   0.8290
   7.750   1.2032   0.01927   0.01252  -0.0742   0.3931   0.8307
   8.000   1.2260   0.01936   0.01272  -0.0736   0.3820   0.8321
   8.250   1.2493   0.01948   0.01285  -0.0731   0.3710   0.8334
   8.500   1.2721   0.01963   0.01300  -0.0725   0.3595   0.8348
   8.750   1.2934   0.01984   0.01329  -0.0717   0.3463   0.8363
   9.000   1.3143   0.02012   0.01361  -0.0709   0.3330   0.8379
   9.250   1.3344   0.02048   0.01399  -0.0700   0.3195   0.8398
   9.500   1.3534   0.02093   0.01443  -0.0690   0.3061   0.8416
   9.750   1.3691   0.02139   0.01489  -0.0674   0.2934   0.8431
  10.000   1.3832   0.02193   0.01540  -0.0655   0.2809   0.8447
  10.250   1.3951   0.02246   0.01598  -0.0633   0.2684   0.8465
  10.500   1.4067   0.02309   0.01666  -0.0612   0.2562   0.8484
  10.750   1.4176   0.02384   0.01744  -0.0592   0.2448   0.8505
  11.000   1.4268   0.02473   0.01830  -0.0571   0.2339   0.8526
  11.250   1.4360   0.02564   0.01926  -0.0551   0.2228   0.8548
  11.500   1.4444   0.02665   0.02034  -0.0532   0.2123   0.8571
  11.750   1.4486   0.02782   0.02150  -0.0509   0.2032   0.8597
  12.000   1.4536   0.02904   0.02280  -0.0489   0.1937   0.8627
  12.250   1.4580   0.03046   0.02429  -0.0472   0.1848   0.8658
  12.500   1.4599   0.03218   0.02600  -0.0457   0.1766   0.8687
  12.750   1.4642   0.03389   0.02784  -0.0446   0.1679   0.8717
  13.000   1.4634   0.03598   0.02988  -0.0433   0.1608   0.8748
  13.250   1.4653   0.03800   0.03207  -0.0425   0.1529   0.8784
  13.500   1.4639   0.04047   0.03451  -0.0418   0.1462   0.8824
  13.750   1.4649   0.04293   0.03713  -0.0417   0.1389   0.8867
  14.000   1.4617   0.04570   0.03986  -0.0412   0.1329   0.8912
  14.250   1.4611   0.04845   0.04280  -0.0413   0.1262   0.8970
  14.500   1.4572   0.05154   0.04587  -0.0413   0.1206   0.9034
  14.750   1.4550   0.05448   0.04901  -0.0415   0.1149   0.9133
  15.000   1.4489   0.05750   0.05213  -0.0413   0.1101   0.9427
  15.250   1.4459   0.06088   0.05556  -0.0420   0.1050   1.0000
  15.500   1.4446   0.06459   0.05939  -0.0434   0.0997   1.0000
  15.750   1.4422   0.06828   0.06298  -0.0445   0.0949   1.0000
  16.000   1.4405   0.07226   0.06716  -0.0461   0.0903   1.0000
  16.250   1.4374   0.07634   0.07130  -0.0477   0.0860   1.0000
  16.500   1.4351   0.08030   0.07526  -0.0491   0.0819   1.0000
  16.750   1.4318   0.08465   0.07976  -0.0510   0.0777   1.0000
  17.000   1.4282   0.08893   0.08404  -0.0527   0.0740   1.0000
  17.250   1.4252   0.09320   0.08839  -0.0544   0.0703   1.0000
  17.500   1.4208   0.09789   0.09320  -0.0566   0.0667   1.0000
  17.750   1.4180   0.10210   0.09736  -0.0584   0.0633   1.0000
  18.000   1.4131   0.10691   0.10231  -0.0606   0.0601   1.0000
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