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NASA/LANGLEY LS(1)-0413 (GA(W)-2) AIRFOIL (ls413-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NASA/LANGLEY LS(1)-0413 (GA(W)-2) AIRFOIL (ls413-il)
Reynolds number: 200,000
Max Cl/Cd: 65.69 at α=3°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ls413-il-200000-n5.txt
Download as CSV file: xf-ls413-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA/LANGLEY LS(1)-0413 (GA(W)-2) 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
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.5923   0.06791   0.06362  -0.0712   1.0000   0.0244
 -11.500  -0.6162   0.06232   0.05795  -0.0740   1.0000   0.0243
 -11.250  -0.6412   0.05841   0.05396  -0.0740   1.0000   0.0242
 -11.000  -0.6696   0.05599   0.05150  -0.0711   1.0000   0.0242
 -10.750  -0.6877   0.05230   0.04764  -0.0719   0.9947   0.0242
 -10.500  -0.6856   0.04698   0.04192  -0.0767   0.9865   0.0241
 -10.250  -0.6755   0.04241   0.03691  -0.0801   0.9812   0.0242
 -10.000  -0.6622   0.03867   0.03274  -0.0820   0.9750   0.0243
  -9.750  -0.6411   0.03538   0.02899  -0.0843   0.9714   0.0244
  -9.500  -0.6175   0.03287   0.02620  -0.0860   0.9676   0.0246
  -9.250  -0.5941   0.03096   0.02409  -0.0869   0.9625   0.0248
  -9.000  -0.5667   0.02926   0.02220  -0.0883   0.9590   0.0251
  -8.750  -0.5373   0.02770   0.02046  -0.0899   0.9564   0.0254
  -8.500  -0.5108   0.02644   0.01903  -0.0906   0.9522   0.0259
  -8.250  -0.4839   0.02533   0.01779  -0.0913   0.9476   0.0265
  -8.000  -0.4545   0.02420   0.01649  -0.0923   0.9442   0.0273
  -7.750  -0.4239   0.02303   0.01515  -0.0934   0.9415   0.0280
  -7.500  -0.3966   0.02200   0.01396  -0.0937   0.9371   0.0286
  -7.250  -0.3693   0.02107   0.01291  -0.0939   0.9323   0.0291
  -7.000  -0.3407   0.02010   0.01190  -0.0945   0.9287   0.0297
  -6.750  -0.3110   0.01926   0.01106  -0.0954   0.9257   0.0305
  -6.500  -0.2840   0.01861   0.01040  -0.0957   0.9210   0.0314
  -6.250  -0.2567   0.01798   0.00975  -0.0960   0.9163   0.0325
  -6.000  -0.2276   0.01738   0.00909  -0.0966   0.9127   0.0339
  -5.750  -0.1977   0.01677   0.00845  -0.0975   0.9097   0.0359
  -5.500  -0.1696   0.01628   0.00797  -0.0980   0.9054   0.0383
  -5.250  -0.1413   0.01583   0.00748  -0.0985   0.9006   0.0409
  -5.000  -0.1114   0.01530   0.00693  -0.0993   0.8967   0.0439
  -4.750  -0.0808   0.01489   0.00649  -0.1001   0.8937   0.0485
  -4.500  -0.0512   0.01449   0.00611  -0.1009   0.8900   0.0557
  -4.250  -0.0220   0.01411   0.00578  -0.1016   0.8856   0.0682
  -4.000   0.0087   0.01356   0.00544  -0.1027   0.8819   0.1096
  -3.750   0.0416   0.01252   0.00504  -0.1051   0.8790   0.2560
  -3.500   0.0757   0.01160   0.00477  -0.1074   0.8766   0.4207
  -3.250   0.1049   0.01125   0.00499  -0.1079   0.8727   0.5530
  -3.000   0.1331   0.01133   0.00518  -0.1078   0.8682   0.6140
  -2.750   0.1609   0.01153   0.00544  -0.1074   0.8643   0.6560
  -2.500   0.1886   0.01175   0.00567  -0.1068   0.8609   0.6838
  -2.250   0.2166   0.01190   0.00578  -0.1066   0.8564   0.6975
  -2.000   0.2443   0.01196   0.00583  -0.1064   0.8519   0.7025
  -1.750   0.2740   0.01199   0.00579  -0.1068   0.8484   0.7077
  -1.500   0.3042   0.01201   0.00576  -0.1072   0.8453   0.7142
  -1.250   0.3316   0.01210   0.00586  -0.1069   0.8413   0.7202
  -1.000   0.3607   0.01217   0.00589  -0.1072   0.8363   0.7267
  -0.750   0.3897   0.01219   0.00590  -0.1073   0.8321   0.7314
  -0.500   0.4184   0.01222   0.00592  -0.1073   0.8286   0.7360
  -0.250   0.4469   0.01230   0.00600  -0.1074   0.8234   0.7419
   0.000   0.4759   0.01229   0.00597  -0.1076   0.8165   0.7467
   0.250   0.5040   0.01224   0.00591  -0.1073   0.8094   0.7497
   0.500   0.5316   0.01221   0.00589  -0.1071   0.7997   0.7527
   0.750   0.5600   0.01216   0.00581  -0.1070   0.7896   0.7561
   1.000   0.5892   0.01206   0.00567  -0.1070   0.7773   0.7598
   1.250   0.6175   0.01201   0.00559  -0.1069   0.7643   0.7628
   1.500   0.6445   0.01198   0.00559  -0.1065   0.7505   0.7652
   1.750   0.6717   0.01197   0.00557  -0.1062   0.7350   0.7682
   2.000   0.6993   0.01197   0.00556  -0.1059   0.7182   0.7714
   2.250   0.7273   0.01199   0.00555  -0.1059   0.7000   0.7748
   2.500   0.7554   0.01203   0.00556  -0.1058   0.6781   0.7783
   2.750   0.7812   0.01211   0.00558  -0.1052   0.6493   0.7809
   3.000   0.8060   0.01227   0.00561  -0.1043   0.6029   0.7837
   3.250   0.8266   0.01274   0.00568  -0.1028   0.5277   0.7869
   3.500   0.8441   0.01354   0.00601  -0.1009   0.4427   0.7908
   3.750   0.8624   0.01436   0.00646  -0.0994   0.3740   0.7946
   4.000   0.8801   0.01511   0.00692  -0.0978   0.3127   0.7973
   4.250   0.8996   0.01578   0.00736  -0.0965   0.2687   0.8004
   4.750   0.9419   0.01697   0.00824  -0.0947   0.2023   0.8081
   5.000   0.9633   0.01751   0.00868  -0.0938   0.1797   0.8117
   5.250   0.9842   0.01801   0.00913  -0.0927   0.1632   0.8150
   5.500   1.0055   0.01851   0.00959  -0.0917   0.1502   0.8188
   5.750   1.0270   0.01903   0.01009  -0.0909   0.1386   0.8229
   6.000   1.0490   0.01950   0.01056  -0.0901   0.1285   0.8268
   6.250   1.0692   0.01998   0.01106  -0.0889   0.1208   0.8304
   6.500   1.0894   0.02049   0.01159  -0.0877   0.1136   0.8347
   6.750   1.1097   0.02104   0.01215  -0.0866   0.1077   0.8398
   7.000   1.1292   0.02155   0.01270  -0.0854   0.1021   0.8443
   7.250   1.1464   0.02218   0.01333  -0.0838   0.0973   0.8492
   7.500   1.1649   0.02269   0.01393  -0.0824   0.0932   0.8546
   7.750   1.1814   0.02323   0.01454  -0.0806   0.0891   0.8597
   8.000   1.1967   0.02390   0.01522  -0.0788   0.0854   0.8653
   8.250   1.2139   0.02458   0.01596  -0.0773   0.0820   0.8716
   8.500   1.2309   0.02516   0.01666  -0.0758   0.0786   0.8777
   8.750   1.2473   0.02585   0.01740  -0.0742   0.0753   0.8851
   9.000   1.2605   0.02669   0.01825  -0.0723   0.0723   0.8932
   9.500   1.2912   0.02800   0.01981  -0.0689   0.0667   0.9148
  10.000   1.3119   0.02949   0.02143  -0.0643   0.0620   1.0000
  10.250   1.3288   0.03048   0.02251  -0.0634   0.0596   1.0000
  10.500   1.3454   0.03146   0.02360  -0.0625   0.0572   1.0000
  10.750   1.3607   0.03250   0.02471  -0.0615   0.0550   1.0000
  11.000   1.3738   0.03368   0.02592  -0.0603   0.0530   1.0000
  11.250   1.3861   0.03498   0.02728  -0.0591   0.0512   1.0000
  11.500   1.3999   0.03618   0.02861  -0.0580   0.0494   1.0000
  11.750   1.4123   0.03747   0.03001  -0.0568   0.0476   1.0000
  12.000   1.4234   0.03885   0.03148  -0.0556   0.0461   1.0000
  12.250   1.4326   0.04038   0.03307  -0.0544   0.0449   1.0000
  12.500   1.4394   0.04219   0.03490  -0.0531   0.0437   1.0000
  12.750   1.4489   0.04380   0.03669  -0.0519   0.0426   1.0000
  13.000   1.4570   0.04555   0.03859  -0.0507   0.0413   1.0000
  13.250   1.4639   0.04740   0.04059  -0.0496   0.0402   1.0000
  13.500   1.4697   0.04936   0.04266  -0.0486   0.0391   1.0000
  13.750   1.4740   0.05147   0.04487  -0.0477   0.0383   1.0000
  14.000   1.4767   0.05378   0.04726  -0.0468   0.0375   1.0000
  14.250   1.4772   0.05640   0.04995  -0.0459   0.0368   1.0000
  14.500   1.4786   0.05904   0.05277  -0.0452   0.0362   1.0000
  14.750   1.4786   0.06190   0.05583  -0.0446   0.0355   1.0000
  15.000   1.4773   0.06500   0.05911  -0.0442   0.0349   1.0000
  15.250   1.4747   0.06834   0.06264  -0.0440   0.0343   1.0000
  15.500   1.4710   0.07194   0.06641  -0.0442   0.0338   1.0000
  15.750   1.4661   0.07580   0.07043  -0.0446   0.0333   1.0000
  16.000   1.4603   0.07994   0.07473  -0.0454   0.0329   1.0000
  16.250   1.4536   0.08437   0.07931  -0.0465   0.0325   1.0000
  16.500   1.4460   0.08910   0.08419  -0.0480   0.0321   1.0000
  16.750   1.4375   0.09414   0.08936  -0.0499   0.0318   1.0000
  17.000   1.4280   0.09950   0.09485  -0.0521   0.0314   1.0000
  17.250   1.4177   0.10515   0.10063  -0.0547   0.0311   1.0000
  17.500   1.4073   0.11094   0.10653  -0.0575   0.0308   1.0000
  17.750   1.3894   0.11860   0.11441  -0.0618   0.0306   1.0000
  18.000   1.3678   0.12742   0.12347  -0.0672   0.0304   1.0000
  18.250   1.3417   0.13770   0.13400  -0.0739   0.0303   1.0000
  18.500   1.3052   0.15117   0.14773  -0.0832   0.0303   1.0000
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