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NASA/LANGLEY NLF(2)-0415 AIRFOIL (nlf415-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NASA/LANGLEY NLF(2)-0415 AIRFOIL (nlf415-il)
Reynolds number: 200,000
Max Cl/Cd: 45.67 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-nlf415-il-200000-n5.txt
Download as CSV file: xf-nlf415-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA/LANGLEY NLF(2)-0415 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.1796   0.09170   0.08766  -0.1260   0.9207   0.0244
 -12.750  -0.1969   0.07986   0.07579  -0.1308   0.9201   0.0177
 -12.500  -0.2028   0.07402   0.06993  -0.1336   0.9190   0.0174
 -12.250  -0.2956   0.07944   0.07521  -0.1363   0.9292   0.0173
 -12.000  -0.3052   0.07361   0.06930  -0.1405   0.9260   0.0171
 -11.750  -0.3177   0.06805   0.06362  -0.1442   0.9228   0.0169
 -11.500  -0.3303   0.06299   0.05841  -0.1474   0.9197   0.0167
 -11.250  -0.3428   0.05896   0.05424  -0.1490   0.9161   0.0165
 -11.000  -0.3584   0.05536   0.05049  -0.1490   0.9119   0.0163
 -10.750  -0.3724   0.05199   0.04693  -0.1486   0.9083   0.0162
 -10.500  -0.3827   0.04897   0.04371  -0.1479   0.9052   0.0160
 -10.250  -0.3945   0.04629   0.04082  -0.1459   0.9020   0.0160
 -10.000  -0.4075   0.04428   0.03864  -0.1424   0.8983   0.0159
  -9.750  -0.4173   0.04231   0.03646  -0.1387   0.8951   0.0159
  -9.500  -0.4197   0.03999   0.03387  -0.1360   0.8928   0.0159
  -9.250  -0.4165   0.03764   0.03124  -0.1338   0.8909   0.0158
  -9.000  -0.4087   0.03547   0.02876  -0.1320   0.8895   0.0161
  -8.750  -0.4008   0.03378   0.02678  -0.1297   0.8875   0.0167
  -8.500  -0.3942   0.03251   0.02522  -0.1267   0.8850   0.0173
  -8.250  -0.3824   0.03103   0.02345  -0.1245   0.8832   0.0175
  -8.000  -0.3660   0.02954   0.02174  -0.1231   0.8818   0.0175
  -7.750  -0.3468   0.02817   0.02016  -0.1220   0.8806   0.0176
  -7.500  -0.3257   0.02703   0.01881  -0.1211   0.8795   0.0178
  -7.250  -0.2978   0.02537   0.01708  -0.1213   0.8790   0.0182
  -7.000  -0.2733   0.02434   0.01599  -0.1209   0.8783   0.0186
  -6.750  -0.2517   0.02358   0.01521  -0.1200   0.8774   0.0190
  -6.500  -0.2331   0.02304   0.01465  -0.1189   0.8765   0.0199
  -6.250  -0.2151   0.02255   0.01413  -0.1176   0.8756   0.0211
  -6.000  -0.1980   0.02202   0.01357  -0.1162   0.8747   0.0218
  -5.750  -0.1917   0.02174   0.01325  -0.1127   0.8728   0.0220
  -5.500  -0.2043   0.02195   0.01346  -0.1056   0.8687   0.0222
  -5.250  -0.2040   0.02182   0.01330  -0.1011   0.8661   0.0225
  -5.000  -0.1966   0.02154   0.01298  -0.0979   0.8642   0.0228
  -4.750  -0.1843   0.02120   0.01259  -0.0958   0.8628   0.0233
  -4.500  -0.1687   0.02078   0.01211  -0.0943   0.8617   0.0240
  -4.250  -0.1484   0.02031   0.01155  -0.0937   0.8607   0.0250
  -4.000  -0.1250   0.01994   0.01112  -0.0936   0.8600   0.0269
  -3.750  -0.1737   0.02124   0.01244  -0.0793   0.8522   0.0260
  -3.500  -0.1550   0.02108   0.01222  -0.0783   0.8504   0.0285
  -3.250  -0.1337   0.02090   0.01201  -0.0777   0.8492   0.0335
  -3.000  -0.1112   0.02069   0.01180  -0.0773   0.8483   0.0454
  -2.750  -0.0944   0.01857   0.01165  -0.0781   0.8474   0.5592
  -2.500  -0.0691   0.01925   0.01230  -0.0774   0.8466   0.5943
  -2.250  -0.0419   0.01970   0.01271  -0.0771   0.8459   0.6092
  -2.000  -0.0152   0.02026   0.01329  -0.0766   0.8453   0.6245
  -1.750  -0.0217   0.02120   0.01423  -0.0706   0.8406   0.6289
  -1.500  -0.0061   0.02168   0.01466  -0.0685   0.8379   0.6373
  -1.250   0.0155   0.02190   0.01485  -0.0678   0.8364   0.6389
  -1.000   0.0403   0.02201   0.01488  -0.0677   0.8351   0.6394
  -0.750   0.0673   0.02207   0.01489  -0.0680   0.8339   0.6400
  -0.500   0.0949   0.02214   0.01491  -0.0684   0.8329   0.6406
  -0.250   0.1225   0.02223   0.01495  -0.0689   0.8321   0.6413
   0.000   0.1515   0.02229   0.01498  -0.0696   0.8313   0.6420
   0.250   0.1816   0.02234   0.01501  -0.0704   0.8307   0.6427
   0.500   0.2119   0.02240   0.01505  -0.0713   0.8301   0.6435
   1.000   0.2279   0.02340   0.01605  -0.0653   0.8208   0.6458
   1.250   0.2554   0.02351   0.01616  -0.0657   0.8193   0.6469
   1.500   0.2841   0.02361   0.01627  -0.0663   0.8181   0.6478
   1.750   0.3137   0.02370   0.01637  -0.0671   0.8171   0.6487
   2.000   0.3444   0.02377   0.01646  -0.0680   0.8163   0.6495
   2.250   0.3757   0.02385   0.01657  -0.0691   0.8155   0.6504
   2.750   0.3994   0.02468   0.01751  -0.0644   0.8050   0.6520
   3.000   0.4292   0.02473   0.01764  -0.0651   0.8035   0.6528
   3.250   0.4852   0.02359   0.01660  -0.0695   0.8013   0.6536
   3.750   0.5354   0.02233   0.01548  -0.0677   0.7801   0.6554
   4.000   0.5841   0.02089   0.01416  -0.0706   0.7740   0.6565
   5.000   0.7184   0.01573   0.00809  -0.0696   0.4830   0.6619
   5.250   0.6992   0.01754   0.00917  -0.0618   0.3527   0.6633
   5.500   0.6970   0.01891   0.01004  -0.0574   0.2588   0.6645
   6.000   0.7195   0.02064   0.01129  -0.0530   0.1576   0.6669
   6.250   0.7358   0.02127   0.01185  -0.0516   0.1310   0.6680
   6.500   0.7532   0.02187   0.01239  -0.0504   0.1120   0.6693
   6.750   0.7713   0.02244   0.01294  -0.0492   0.0981   0.6706
   7.000   0.7898   0.02301   0.01351  -0.0482   0.0874   0.6721
   7.250   0.8087   0.02356   0.01413  -0.0472   0.0793   0.6737
   7.500   0.8267   0.02422   0.01477  -0.0461   0.0719   0.6753
   7.750   0.8463   0.02476   0.01540  -0.0453   0.0658   0.6771
   8.000   0.8644   0.02546   0.01611  -0.0442   0.0609   0.6789
   8.500   0.9024   0.02670   0.01754  -0.0424   0.0523   0.6824
   8.750   0.9200   0.02746   0.01831  -0.0413   0.0477   0.6842
   9.000   0.9406   0.02793   0.01891  -0.0407   0.0426   0.6865
   9.250   0.9588   0.02864   0.01962  -0.0399   0.0379   0.6888
   9.500   0.9790   0.02920   0.02033  -0.0392   0.0336   0.6915
   9.750   0.9973   0.02996   0.02112  -0.0384   0.0299   0.6941
  10.000   1.0160   0.03072   0.02202  -0.0375   0.0266   0.6965
  10.250   1.0336   0.03154   0.02292  -0.0366   0.0234   0.6988
  10.500   1.0503   0.03257   0.02408  -0.0355   0.0208   0.7014
  10.750   1.0670   0.03357   0.02521  -0.0345   0.0186   0.7043
  11.000   1.0820   0.03470   0.02642  -0.0334   0.0173   0.7075
  11.500   1.1130   0.03709   0.02917  -0.0312   0.0147   0.7139
  11.750   1.1270   0.03825   0.03046  -0.0301   0.0138   0.7175
  12.000   1.1387   0.03964   0.03197  -0.0288   0.0131   0.7216
  12.500   1.1598   0.04317   0.03595  -0.0260   0.0121   0.7299
  12.750   1.1682   0.04513   0.03818  -0.0245   0.0117   0.7349
  13.250   1.1788   0.04952   0.04310  -0.0212   0.0111   0.7463
  13.500   1.1804   0.05199   0.04582  -0.0195   0.0109   0.7532
  13.750   1.1795   0.05469   0.04879  -0.0178   0.0107   0.7605
  14.000   1.1763   0.05760   0.05197  -0.0162   0.0105   0.7691
  14.250   1.1705   0.06078   0.05542  -0.0147   0.0104   0.7789
  14.500   1.1617   0.06440   0.05933  -0.0134   0.0103   0.7904
  14.750   1.1509   0.06830   0.06351  -0.0125   0.0102   0.8053
  15.000   1.1372   0.07266   0.06817  -0.0119   0.0101   0.8268
  15.250   1.1187   0.07720   0.07313  -0.0111   0.0101   0.9015
  15.500   1.0959   0.08342   0.07963  -0.0123   0.0101   1.0000
  15.750   1.0714   0.09120   0.08768  -0.0153   0.0102   1.0000
  16.000   1.0396   0.10167   0.09843  -0.0209   0.0102   1.0000
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