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NASA/LANGLEY NLF 0414F AIRFOIL (nlf414f-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NASA/LANGLEY NLF 0414F AIRFOIL (nlf414f-il)
Reynolds number: 100,000
Max Cl/Cd: 35.88 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-nlf414f-il-100000.txt
Download as CSV file: xf-nlf414f-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA/LANGLEY NLF 0414F 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.5018   0.12201   0.11754  -0.0304   1.0000   0.1042
  -9.750  -0.5057   0.11936   0.11492  -0.0297   1.0000   0.1077
  -9.500  -0.5215   0.11617   0.11178  -0.0305   1.0000   0.1112
  -9.250  -0.5548   0.11233   0.10802  -0.0334   1.0000   0.1130
  -9.000  -0.5891   0.10812   0.10387  -0.0356   1.0000   0.1134
  -8.750  -0.6222   0.10505   0.10081  -0.0347   1.0000   0.1135
  -8.500  -0.5616   0.10292   0.09870  -0.0286   1.0000   0.1210
  -8.250  -0.5802   0.09947   0.09529  -0.0285   1.0000   0.1236
  -8.000  -0.6111   0.09583   0.09169  -0.0281   1.0000   0.1246
  -7.750  -0.6432   0.09235   0.08821  -0.0272   1.0000   0.1253
  -7.500  -0.6780   0.08830   0.08403  -0.0279   1.0000   0.1278
  -7.250  -0.5858   0.08284   0.07905  -0.0243   1.0000   0.1424
  -7.000  -0.6876   0.08066   0.07636  -0.0255   1.0000   0.1350
  -6.750  -0.6905   0.07763   0.07324  -0.0247   1.0000   0.1415
  -6.500  -0.6986   0.07325   0.06867  -0.0249   1.0000   0.1491
  -6.250  -0.6898   0.07066   0.06609  -0.0233   1.0000   0.1556
  -6.000  -0.6879   0.06698   0.06226  -0.0233   1.0000   0.1669
  -5.750  -0.6822   0.06391   0.05901  -0.0232   1.0000   0.1818
  -5.500  -0.6727   0.06116   0.05618  -0.0227   1.0000   0.1981
  -5.250  -0.6614   0.05849   0.05350  -0.0218   1.0000   0.2156
  -5.000  -0.6489   0.05604   0.05109  -0.0206   1.0000   0.2348
  -4.750  -0.5814   0.04312   0.03538  -0.0261   1.0000   0.0819
  -4.500  -0.5535   0.03964   0.03120  -0.0254   1.0000   0.0693
  -4.250  -0.5289   0.03711   0.02839  -0.0252   1.0000   0.0661
  -4.000  -0.5037   0.03530   0.02622  -0.0248   1.0000   0.0650
  -3.750  -0.4792   0.03400   0.02467  -0.0244   1.0000   0.0661
  -3.500  -0.4544   0.03281   0.02326  -0.0239   1.0000   0.0669
  -3.250  -0.4295   0.03170   0.02199  -0.0233   1.0000   0.0672
  -3.000  -0.4047   0.03080   0.02097  -0.0228   1.0000   0.0684
  -2.750  -0.3801   0.03012   0.02019  -0.0222   1.0000   0.0704
  -2.500  -0.3548   0.02921   0.01941  -0.0222   1.0000   0.0749
  -2.250  -0.3298   0.02881   0.01905  -0.0222   1.0000   0.0834
  -2.000  -0.3021   0.02820   0.01854  -0.0228   1.0000   0.0963
  -1.750  -0.2704   0.02599   0.01967  -0.0231   1.0000   0.6202
  -1.500  -0.2801   0.02799   0.02165  -0.0114   1.0000   0.8122
  -1.250  -0.2868   0.02829   0.02195  -0.0018   1.0000   0.8552
  -1.000  -0.1484   0.03178   0.02509  -0.0135   1.0000   1.0000
  -0.750  -0.1410   0.03166   0.02486  -0.0113   1.0000   1.0000
  -0.500  -0.1336   0.03156   0.02466  -0.0090   1.0000   1.0000
  -0.250  -0.1261   0.03148   0.02449  -0.0068   1.0000   1.0000
   0.000  -0.1186   0.03141   0.02435  -0.0046   1.0000   1.0000
   0.250  -0.1111   0.03136   0.02423  -0.0024   1.0000   1.0000
   0.500  -0.1036   0.03133   0.02413  -0.0002   1.0000   1.0000
   0.750  -0.0959   0.03131   0.02406   0.0019   1.0000   1.0000
   1.000  -0.0879   0.03132   0.02402   0.0039   1.0000   1.0000
   1.250  -0.0798   0.03136   0.02401   0.0058   1.0000   1.0000
   1.500  -0.0643   0.03167   0.02428   0.0063   0.9984   1.0000
   1.750  -0.0235   0.03302   0.02556   0.0019   0.9879   1.0000
   2.000   0.0149   0.03432   0.02680  -0.0019   0.9757   1.0000
   2.250   0.0504   0.03551   0.02795  -0.0050   0.9623   1.0000
   2.500   0.0835   0.03662   0.02904  -0.0076   0.9484   1.0000
   2.750   0.1152   0.03770   0.03010  -0.0098   0.9344   1.0000
   3.000   0.1460   0.03876   0.03117  -0.0118   0.9203   1.0000
   3.250   0.1774   0.03984   0.03225  -0.0138   0.9056   1.0000
   3.500   0.2103   0.04092   0.03335  -0.0159   0.8899   1.0000
   3.750   0.2486   0.04207   0.03452  -0.0186   0.8727   1.0000
   4.000   0.3166   0.04223   0.03470  -0.0232   0.8275   1.0000
   4.250   0.3646   0.04271   0.03522  -0.0262   0.8101   1.0000
   4.500   0.3967   0.04291   0.03548  -0.0271   0.7950   1.0000
   4.750   0.4245   0.04306   0.03572  -0.0275   0.7806   1.0000
   5.000   0.4546   0.04314   0.03588  -0.0282   0.7664   1.0000
   5.250   0.5005   0.04242   0.03525  -0.0299   0.7504   1.0000
   5.500   0.5529   0.04096   0.03392  -0.0318   0.7351   1.0000
   5.750   0.5920   0.03992   0.03301  -0.0326   0.7218   1.0000
   6.000   0.6301   0.03873   0.03196  -0.0332   0.7089   1.0000
   6.250   0.6721   0.03688   0.03030  -0.0335   0.6952   1.0000
   6.500   0.7185   0.03414   0.02774  -0.0336   0.6800   1.0000
   6.750   0.7447   0.03250   0.02628  -0.0320   0.6578   1.0000
   7.000   0.7840   0.02973   0.02371  -0.0310   0.6362   1.0000
   7.250   0.8082   0.02823   0.02236  -0.0291   0.5974   1.0000
   7.500   0.8590   0.02394   0.01653  -0.0252   0.3456   1.0000
   7.750   0.8521   0.02634   0.01775  -0.0213   0.2158   1.0000
   8.000   0.8595   0.02818   0.01900  -0.0192   0.1662   1.0000
   8.250   0.8760   0.02953   0.02014  -0.0181   0.1397   1.0000
   8.500   0.8981   0.03074   0.02118  -0.0176   0.1236   1.0000
   8.750   0.9259   0.03185   0.02222  -0.0176   0.1117   1.0000
   9.000   0.9592   0.03306   0.02336  -0.0182   0.1025   1.0000
   9.250   0.9959   0.03432   0.02459  -0.0193   0.0957   1.0000
   9.500   1.0400   0.03611   0.02644  -0.0211   0.0898   1.0000
   9.750   1.0732   0.03771   0.02822  -0.0220   0.0851   1.0000
  10.000   1.1143   0.03994   0.03051  -0.0241   0.0818   1.0000
  10.250   1.1548   0.04347   0.03423  -0.0263   0.0794   1.0000
  10.500   1.1706   0.04557   0.03678  -0.0252   0.0777   1.0000
  10.750   1.1853   0.04809   0.03971  -0.0241   0.0762   1.0000
  11.000   1.1984   0.05120   0.04322  -0.0230   0.0756   1.0000
  11.250   1.2058   0.05459   0.04702  -0.0214   0.0755   1.0000
  11.500   1.2069   0.05816   0.05097  -0.0193   0.0759   1.0000
  11.750   1.2029   0.06187   0.05503  -0.0170   0.0764   1.0000
  12.000   1.1946   0.06566   0.05915  -0.0146   0.0768   1.0000
  12.250   1.1827   0.06959   0.06337  -0.0123   0.0773   1.0000
  12.500   1.1682   0.07373   0.06776  -0.0102   0.0777   1.0000
  12.750   1.1519   0.07813   0.07239  -0.0085   0.0782   1.0000
  13.000   1.1362   0.08293   0.07738  -0.0073   0.0788   1.0000
  13.250   1.1288   0.08853   0.08311  -0.0069   0.0796   1.0000
  13.500   0.8934   0.12369   0.11924  -0.0228   0.1099   1.0000
  13.750   0.9738   0.11072   0.10618  -0.0116   0.0946   1.0000
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