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NASA/LANGLEY NLF(1)-0215F AIRFOIL (nlf0215f-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NASA/LANGLEY NLF(1)-0215F AIRFOIL (nlf0215f-il)
Reynolds number: 100,000
Max Cl/Cd: 49.44 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-nlf0215f-il-100000-n5.txt
Download as CSV file: xf-nlf0215f-il-100000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.2799   0.07273   0.06788  -0.0907   0.9397   0.0330
  -8.500  -0.2775   0.06818   0.06328  -0.0946   0.9266   0.0325
  -8.250  -0.2803   0.06339   0.05839  -0.0987   0.9123   0.0319
  -8.000  -0.2788   0.05802   0.05282  -0.1038   0.8985   0.0313
  -7.750  -0.2722   0.05259   0.04706  -0.1084   0.8875   0.0306
  -7.500  -0.2610   0.04756   0.04161  -0.1118   0.8771   0.0298
  -7.250  -0.2488   0.04301   0.03658  -0.1138   0.8659   0.0291
  -7.000  -0.2260   0.03872   0.03170  -0.1165   0.8587   0.0286
  -6.750  -0.2052   0.03563   0.02813  -0.1174   0.8485   0.0285
  -6.500  -0.1759   0.03284   0.02485  -0.1192   0.8415   0.0285
  -6.250  -0.1499   0.03074   0.02238  -0.1199   0.8325   0.0288
  -6.000  -0.1177   0.02898   0.02029  -0.1216   0.8261   0.0297
  -5.750  -0.0913   0.02760   0.01864  -0.1218   0.8174   0.0311
  -5.500  -0.0584   0.02613   0.01682  -0.1229   0.8117   0.0326
  -5.250  -0.0325   0.02497   0.01542  -0.1226   0.8039   0.0332
  -5.000  -0.0033   0.02377   0.01410  -0.1228   0.7977   0.0339
  -4.750   0.0239   0.02282   0.01312  -0.1229   0.7914   0.0350
  -4.500   0.0494   0.02207   0.01233  -0.1226   0.7844   0.0364
  -4.250   0.0787   0.02133   0.01149  -0.1230   0.7793   0.0383
  -4.000   0.1022   0.02084   0.01092  -0.1224   0.7727   0.0414
  -3.750   0.1282   0.02030   0.01039  -0.1224   0.7672   0.0458
  -3.500   0.1576   0.01979   0.00974  -0.1229   0.7628   0.0509
  -3.250   0.1805   0.01939   0.00933  -0.1222   0.7567   0.0597
  -3.000   0.2054   0.01877   0.00896  -0.1220   0.7514   0.1007
  -2.750   0.2298   0.01687   0.00875  -0.1236   0.7472   0.4575
  -2.500   0.2377   0.01849   0.01094  -0.1164   0.7421   0.6678
  -2.000   0.2692   0.02063   0.01292  -0.1074   0.7331   0.7451
  -1.750   0.2856   0.02113   0.01330  -0.1033   0.7296   0.7658
  -1.500   0.3008   0.02133   0.01344  -0.1002   0.7242   0.7785
  -1.250   0.3259   0.02135   0.01332  -0.1000   0.7200   0.7861
  -1.000   0.3532   0.02130   0.01311  -0.1001   0.7165   0.7904
  -0.750   0.3814   0.02125   0.01290  -0.1002   0.7134   0.7938
  -0.500   0.4023   0.02130   0.01290  -0.0994   0.7084   0.7976
  -0.250   0.4296   0.02133   0.01282  -0.0999   0.7043   0.8011
   0.000   0.4594   0.02133   0.01271  -0.1009   0.7009   0.8038
   0.250   0.4888   0.02128   0.01255  -0.1013   0.6981   0.8057
   0.500   0.5098   0.02138   0.01264  -0.1005   0.6936   0.8080
   0.750   0.5340   0.02147   0.01269  -0.1003   0.6893   0.8102
   1.000   0.5624   0.02153   0.01269  -0.1009   0.6859   0.8122
   1.250   0.5938   0.02157   0.01265  -0.1020   0.6829   0.8141
   1.500   0.6217   0.02170   0.01275  -0.1026   0.6793   0.8160
   1.750   0.6460   0.02193   0.01299  -0.1028   0.6748   0.8175
   2.000   0.6728   0.02205   0.01310  -0.1030   0.6710   0.8190
   2.250   0.7014   0.02211   0.01314  -0.1035   0.6678   0.8203
   2.750   0.7507   0.02250   0.01359  -0.1034   0.6599   0.8225
   3.000   0.7756   0.02270   0.01381  -0.1033   0.6556   0.8240
   3.250   0.8053   0.02281   0.01393  -0.1040   0.6522   0.8254
   3.500   0.8387   0.02286   0.01397  -0.1054   0.6493   0.8263
   3.750   0.8555   0.02330   0.01452  -0.1041   0.6433   0.8274
   4.000   0.8819   0.02350   0.01477  -0.1044   0.6386   0.8285
   4.250   0.9145   0.02355   0.01484  -0.1056   0.6348   0.8298
   4.500   0.9383   0.02383   0.01520  -0.1054   0.6294   0.8312
   4.750   0.9617   0.02410   0.01554  -0.1052   0.6232   0.8322
   5.000   0.9959   0.02405   0.01553  -0.1065   0.6186   0.8330
   5.250   1.0151   0.02434   0.01593  -0.1055   0.6116   0.8338
   5.500   1.0412   0.02437   0.01603  -0.1053   0.6049   0.8346
   5.750   1.0702   0.02432   0.01602  -0.1057   0.5989   0.8356
   6.000   1.0874   0.02457   0.01643  -0.1041   0.5905   0.8370
   6.250   1.1201   0.02435   0.01623  -0.1049   0.5840   0.8382
   6.500   1.1343   0.02465   0.01669  -0.1030   0.5742   0.8395
   6.750   1.1600   0.02461   0.01674  -0.1027   0.5657   0.8405
   7.000   1.1810   0.02467   0.01690  -0.1017   0.5559   0.8415
   7.250   1.1965   0.02492   0.01729  -0.1000   0.5453   0.8427
   7.500   1.2184   0.02492   0.01738  -0.0991   0.5347   0.8438
   7.750   1.2356   0.02499   0.01756  -0.0974   0.5227   0.8450
   8.000   1.2449   0.02539   0.01808  -0.0947   0.5090   0.8465
   8.250   1.2574   0.02575   0.01854  -0.0926   0.4938   0.8481
   8.500   1.2687   0.02609   0.01897  -0.0902   0.4772   0.8497
   8.750   1.2770   0.02665   0.01960  -0.0876   0.4579   0.8513
   9.000   1.2875   0.02719   0.02017  -0.0853   0.4349   0.8528
   9.250   1.2974   0.02786   0.02079  -0.0831   0.4086   0.8542
   9.500   1.3046   0.02878   0.02161  -0.0808   0.3798   0.8556
   9.750   1.3082   0.03007   0.02276  -0.0783   0.3505   0.8571
  10.000   1.3093   0.03168   0.02424  -0.0759   0.3232   0.8587
  10.250   1.3094   0.03354   0.02602  -0.0738   0.2972   0.8602
  10.500   1.3093   0.03557   0.02796  -0.0719   0.2738   0.8617
  10.750   1.3095   0.03766   0.03000  -0.0703   0.2524   0.8631
  11.000   1.3093   0.03983   0.03211  -0.0687   0.2334   0.8646
  11.250   1.3098   0.04206   0.03430  -0.0674   0.2158   0.8663
  11.500   1.3116   0.04426   0.03650  -0.0662   0.1999   0.8682
  11.750   1.3137   0.04654   0.03876  -0.0653   0.1852   0.8702
  12.000   1.3159   0.04888   0.04111  -0.0645   0.1720   0.8722
  12.250   1.3194   0.05118   0.04344  -0.0638   0.1595   0.8744
  12.500   1.3239   0.05348   0.04578  -0.0633   0.1485   0.8764
  12.750   1.3273   0.05583   0.04817  -0.0628   0.1389   0.8783
  13.000   1.3296   0.05834   0.05070  -0.0623   0.1303   0.8803
  13.250   1.3350   0.06063   0.05309  -0.0619   0.1218   0.8825
  13.500   1.3374   0.06328   0.05573  -0.0616   0.1152   0.8848
  13.750   1.3433   0.06563   0.05824  -0.0614   0.1080   0.8873
  14.000   1.3453   0.06842   0.06103  -0.0614   0.1026   0.8899
  14.250   1.3516   0.07077   0.06355  -0.0612   0.0967   0.8928
  14.500   1.3543   0.07351   0.06636  -0.0612   0.0919   0.8960
  14.750   1.3583   0.07613   0.06907  -0.0611   0.0875   0.8998
  15.000   1.3625   0.07880   0.07190  -0.0612   0.0828   0.9042
  15.250   1.3642   0.08169   0.07485  -0.0613   0.0792   0.9097
  15.500   1.3675   0.08436   0.07766  -0.0612   0.0757   0.9175
  16.000   1.3699   0.09013   0.08374  -0.0618   0.0689   1.0000
  16.250   1.3732   0.09328   0.08688  -0.0626   0.0661   1.0000
  16.500   1.3763   0.09670   0.09056  -0.0636   0.0629   1.0000
  16.750   1.3777   0.10035   0.09436  -0.0648   0.0599   1.0000
  17.000   1.3781   0.10410   0.09817  -0.0662   0.0573   1.0000
  17.250   1.3792   0.10776   0.10192  -0.0675   0.0549   1.0000
  17.500   1.3774   0.11209   0.10650  -0.0693   0.0522   1.0000
  17.750   1.3754   0.11646   0.11101  -0.0713   0.0498   1.0000
  18.000   1.3737   0.12072   0.11537  -0.0735   0.0477   1.0000
  18.250   1.3714   0.12514   0.11988  -0.0757   0.0457   1.0000
  18.500   1.3656   0.13046   0.12546  -0.0785   0.0437   1.0000
  18.750   1.3606   0.13563   0.13081  -0.0814   0.0418   1.0000
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