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NASA/LANGLEY NLF(2)-0415 AIRFOIL (nlf415-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NASA/LANGLEY NLF(2)-0415 AIRFOIL (nlf415-il)
Reynolds number: 500,000
Max Cl/Cd: 85.28 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-nlf415-il-500000.txt
Download as CSV file: xf-nlf415-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.2281   0.08789   0.08508  -0.1439   0.9309   0.0188
 -12.500  -0.2260   0.08325   0.08042  -0.1473   0.9270   0.0193
 -12.250  -0.2359   0.07498   0.07210  -0.1537   0.9228   0.0194
 -12.000  -0.2626   0.06633   0.06329  -0.1595   0.9183   0.0191
 -11.250  -0.2461   0.04504   0.04195  -0.1526   0.9021   0.0212
 -11.000  -0.2670   0.04115   0.03796  -0.1525   0.9001   0.0214
 -10.750  -0.2870   0.03767   0.03438  -0.1518   0.8979   0.0212
 -10.500  -0.3034   0.03516   0.03172  -0.1505   0.8956   0.0223
 -10.250  -0.3204   0.03268   0.02909  -0.1485   0.8932   0.0225
 -10.000  -0.3410   0.03344   0.02960  -0.1441   0.8900   0.0235
  -9.750  -0.3562   0.03218   0.02817  -0.1399   0.8880   0.0236
  -9.500  -0.3656   0.03050   0.02631  -0.1365   0.8864   0.0236
  -6.750  -0.2309   0.02045   0.01397  -0.1289   0.8769   0.0241
  -6.500  -0.1983   0.01880   0.01234  -0.1296   0.8767   0.0226
  -6.250  -0.1733   0.01781   0.01132  -0.1291   0.8761   0.0223
  -6.000  -0.1532   0.01716   0.01063  -0.1279   0.8753   0.0223
  -5.750  -0.1361   0.01673   0.01017  -0.1264   0.8745   0.0227
  -5.500  -0.1231   0.01633   0.00975  -0.1242   0.8736   0.0227
  -5.250  -0.1110   0.01605   0.00945  -0.1219   0.8727   0.0231
  -5.000  -0.0961   0.01595   0.00934  -0.1200   0.8717   0.0237
  -4.750  -0.0884   0.01560   0.00896  -0.1169   0.8703   0.0240
  -4.500  -0.0787   0.01534   0.00867  -0.1141   0.8688   0.0245
  -4.250  -0.0655   0.01519   0.00848  -0.1119   0.8674   0.0250
  -4.000  -0.0495   0.01504   0.00830  -0.1102   0.8660   0.0262
  -3.750  -0.0324   0.01502   0.00825  -0.1086   0.8649   0.0276
  -3.500  -0.0136   0.01503   0.00822  -0.1073   0.8640   0.0299
  -3.250   0.0063   0.01500   0.00819  -0.1062   0.8631   0.0372
  -3.000   0.0118   0.01263   0.00758  -0.1049   0.8619   0.5454
  -2.750  -0.0433   0.01718   0.01038  -0.0866   0.8540   0.0417
  -2.500   0.0069   0.01474   0.00969  -0.0934   0.8564   0.5899
  -2.250   0.0534   0.01504   0.01007  -0.0968   0.8575   0.6097
  -2.000  -0.0023   0.01673   0.01169  -0.0814   0.8488   0.6062
  -1.750   0.0221   0.01713   0.01215  -0.0809   0.8480   0.6140
  -1.500   0.0484   0.01749   0.01246  -0.0808   0.8474   0.6216
  -1.250   0.0770   0.01772   0.01274  -0.0810   0.8468   0.6268
  -1.000   0.1072   0.01810   0.01310  -0.0815   0.8463   0.6354
  -0.750   0.1370   0.01817   0.01321  -0.0821   0.8459   0.6390
  -0.500   0.1457   0.01883   0.01386  -0.0790   0.8431   0.6397
  -0.250   0.1865   0.01865   0.01364  -0.0818   0.8438   0.6401
   0.000   0.2252   0.01851   0.01349  -0.0843   0.8442   0.6405
   0.250   0.2634   0.01840   0.01337  -0.0867   0.8446   0.6410
   0.500   0.2172   0.01996   0.01493  -0.0735   0.8330   0.6419
   0.750   0.2489   0.01998   0.01495  -0.0746   0.8323   0.6424
   1.000   0.2803   0.02003   0.01499  -0.0756   0.8317   0.6430
   1.250   0.3127   0.02006   0.01504  -0.0769   0.8312   0.6436
   1.500   0.3458   0.02009   0.01508  -0.0782   0.8308   0.6443
   1.750   0.3796   0.02012   0.01513  -0.0797   0.8304   0.6449
   2.000   0.4288   0.01946   0.01451  -0.0837   0.8298   0.6456
   2.250   0.5654   0.01525   0.01035  -0.1031   0.8291   0.6463
   2.500   0.5338   0.01626   0.01137  -0.0917   0.8189   0.6474
   2.750   0.6492   0.01356   0.00873  -0.1082   0.8197   0.6482
   3.000   0.7318   0.01173   0.00689  -0.1186   0.8153   0.6489
   3.250   0.7470   0.01143   0.00665  -0.1158   0.8064   0.6497
   3.500   0.7844   0.01069   0.00591  -0.1174   0.7975   0.6504
   3.750   0.8120   0.01007   0.00533  -0.1170   0.7854   0.6512
   4.000   0.8220   0.00977   0.00510  -0.1130   0.7701   0.6521
   4.250   0.8212   0.00963   0.00503  -0.1068   0.7484   0.6530
   4.500   0.8017   0.00981   0.00452  -0.0962   0.6127   0.6538
   4.750   0.7655   0.01135   0.00551  -0.0837   0.5073   0.6547
   5.000   0.7407   0.01296   0.00661  -0.0743   0.4016   0.6556
   5.250   0.7309   0.01441   0.00754  -0.0681   0.2963   0.6565
   5.500   0.7338   0.01551   0.00823  -0.0643   0.2131   0.6575
   5.750   0.7456   0.01627   0.00875  -0.0621   0.1624   0.6586
   6.000   0.7609   0.01690   0.00923  -0.0604   0.1299   0.6597
   6.250   0.7780   0.01744   0.00968  -0.0590   0.1074   0.6609
   6.500   0.7961   0.01796   0.01013  -0.0577   0.0916   0.6621
   6.750   0.8147   0.01846   0.01060  -0.0566   0.0802   0.6635
   7.000   0.8327   0.01903   0.01113  -0.0554   0.0710   0.6648
   7.250   0.8527   0.01945   0.01155  -0.0545   0.0639   0.6660
   7.500   0.8713   0.01995   0.01207  -0.0534   0.0578   0.6673
   7.750   0.8915   0.02035   0.01250  -0.0526   0.0528   0.6687
   8.000   0.9086   0.02100   0.01316  -0.0513   0.0480   0.6701
   8.250   0.9298   0.02135   0.01360  -0.0506   0.0452   0.6715
   8.500   0.9499   0.02180   0.01408  -0.0498   0.0421   0.6731
   8.750   0.9665   0.02256   0.01485  -0.0485   0.0379   0.6748
   9.000   0.9885   0.02285   0.01521  -0.0480   0.0349   0.6766
   9.250   1.0071   0.02345   0.01579  -0.0471   0.0300   0.6783
   9.500   1.0281   0.02386   0.01623  -0.0465   0.0249   0.6801
   9.750   1.0459   0.02459   0.01699  -0.0454   0.0201   0.6820
  10.000   1.0615   0.02553   0.01795  -0.0441   0.0171   0.6839
  10.250   1.0797   0.02623   0.01875  -0.0430   0.0157   0.6860
  10.500   1.0970   0.02700   0.01960  -0.0420   0.0145   0.6883
  10.750   1.1127   0.02795   0.02062  -0.0407   0.0136   0.6906
  11.000   1.1244   0.02945   0.02221  -0.0390   0.0128   0.6930
  11.250   1.1407   0.03043   0.02331  -0.0378   0.0125   0.6956
  11.500   1.1559   0.03154   0.02457  -0.0365   0.0121   0.6984
  11.750   1.1708   0.03272   0.02591  -0.0353   0.0118   0.7015
  12.000   1.1851   0.03395   0.02728  -0.0340   0.0114   0.7049
  12.250   1.1983   0.03531   0.02878  -0.0327   0.0111   0.7085
  12.500   1.2104   0.03651   0.03009  -0.0313   0.0106   0.7121
  12.750   1.2210   0.03796   0.03168  -0.0299   0.0103   0.7160
  13.000   1.2303   0.03956   0.03342  -0.0284   0.0101   0.7204
  13.250   1.2362   0.04178   0.03583  -0.0266   0.0098   0.7250
  13.500   1.2384   0.04455   0.03886  -0.0247   0.0097   0.7294
  13.750   1.2368   0.04761   0.04220  -0.0225   0.0096   0.7346
  14.000   1.2314   0.05097   0.04585  -0.0203   0.0095   0.7401
  14.250   1.2254   0.05403   0.04918  -0.0183   0.0095   0.7465
  14.500   1.2178   0.05731   0.05271  -0.0166   0.0095   0.7543
  14.750   1.2069   0.06103   0.05672  -0.0150   0.0094   0.7630
  15.000   1.1938   0.06516   0.06113  -0.0138   0.0094   0.7737
  15.250   1.1761   0.07015   0.06639  -0.0132   0.0094   0.7867
  15.500   1.1586   0.07531   0.07186  -0.0133   0.0094   0.8071
  15.750   1.1383   0.08097   0.07788  -0.0138   0.0094   0.8517
  16.000   1.1090   0.08840   0.08569  -0.0157   0.0095   1.0000
  16.250   1.0859   0.09651   0.09398  -0.0195   0.0095   1.0000
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