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NASA/LANGLEY LS(1)-0421MOD AIRFOIL (ls421mod-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NASA/LANGLEY LS(1)-0421MOD AIRFOIL (ls421mod-il)
Reynolds number: 50,000
Max Cl/Cd: 18.63 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ls421mod-il-50000-n5.txt
Download as CSV file: xf-ls421mod-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA/LANGLEY LS(1)-0421MOD AIRFOIL              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.500  -0.4792   0.11665   0.10810  -0.0490   1.0000   0.0833
 -14.250  -0.5822   0.09200   0.08310  -0.0633   1.0000   0.0830
 -14.000  -0.6380   0.08076   0.07154  -0.0690   1.0000   0.0829
 -13.750  -0.6731   0.07369   0.06417  -0.0716   1.0000   0.0832
 -13.500  -0.6997   0.06828   0.05845  -0.0727   1.0000   0.0839
 -13.250  -0.6987   0.06572   0.05588  -0.0726   1.0000   0.0853
 -13.000  -0.6966   0.06346   0.05360  -0.0722   1.0000   0.0869
 -12.750  -0.7006   0.06081   0.05083  -0.0716   1.0000   0.0887
 -12.500  -0.7073   0.05811   0.04795  -0.0706   1.0000   0.0905
 -12.250  -0.7157   0.05554   0.04513  -0.0691   1.0000   0.0923
 -12.000  -0.7053   0.05434   0.04406  -0.0677   1.0000   0.0944
 -11.750  -0.7020   0.05303   0.04276  -0.0657   1.0000   0.0966
 -11.500  -0.7042   0.05166   0.04131  -0.0632   1.0000   0.0990
 -11.250  -0.7111   0.05035   0.03985  -0.0600   1.0000   0.1015
 -11.000  -0.7098   0.04972   0.03935  -0.0570   1.0000   0.1038
 -10.750  -0.7152   0.04905   0.03872  -0.0534   1.0000   0.1062
 -10.500  -0.7224   0.04836   0.03796  -0.0495   1.0000   0.1089
 -10.250  -0.7286   0.04768   0.03722  -0.0456   1.0000   0.1117
 -10.000  -0.7093   0.04675   0.03638  -0.0457   0.9953   0.1167
  -9.750  -0.6763   0.04552   0.03510  -0.0478   0.9881   0.1245
  -9.500  -0.6457   0.04433   0.03384  -0.0497   0.9801   0.1339
  -9.250  -0.6176   0.04323   0.03281  -0.0513   0.9719   0.1437
  -9.000  -0.5894   0.04209   0.03172  -0.0530   0.9635   0.1555
  -8.750  -0.5654   0.04099   0.03069  -0.0540   0.9542   0.1688
  -8.500  -0.5387   0.03981   0.02959  -0.0556   0.9460   0.1851
  -8.250  -0.5171   0.03870   0.02857  -0.0563   0.9362   0.2029
  -8.000  -0.4913   0.03749   0.02748  -0.0579   0.9278   0.2254
  -7.750  -0.4722   0.03640   0.02660  -0.0582   0.9180   0.2486
  -7.500  -0.4511   0.03531   0.02568  -0.0589   0.9088   0.2778
  -7.250  -0.4312   0.03440   0.02503  -0.0589   0.8996   0.3108
  -7.000  -0.4125   0.03373   0.02460  -0.0584   0.8894   0.3483
  -6.750  -0.3801   0.03346   0.02465  -0.0588   0.8835   0.3950
  -6.500  -0.3611   0.03396   0.02538  -0.0563   0.8720   0.4314
  -6.250  -0.3245   0.03481   0.02633  -0.0558   0.8650   0.4695
  -6.000  -0.2930   0.03568   0.02717  -0.0548   0.8573   0.4994
  -5.750  -0.2735   0.03614   0.02755  -0.0532   0.8466   0.5248
  -5.500  -0.2382   0.03686   0.02813  -0.0531   0.8402   0.5467
  -5.250  -0.2226   0.03739   0.02857  -0.0509   0.8292   0.5658
  -5.000  -0.1964   0.03781   0.02886  -0.0501   0.8210   0.5847
  -4.750  -0.1542   0.03882   0.02973  -0.0499   0.8159   0.5963
  -4.500  -0.1428   0.03934   0.03019  -0.0471   0.8036   0.6102
  -4.250  -0.1170   0.03938   0.03009  -0.0467   0.7964   0.6266
  -4.000  -0.0885   0.04010   0.03072  -0.0452   0.7882   0.6370
  -3.750  -0.0697   0.04040   0.03094  -0.0434   0.7783   0.6505
  -3.500  -0.0443   0.04024   0.03064  -0.0431   0.7721   0.6666
  -3.250  -0.0213   0.04093   0.03129  -0.0410   0.7619   0.6737
  -2.750   0.0346   0.04074   0.03088  -0.0400   0.7484   0.6948
  -2.500   0.0376   0.04095   0.03106  -0.0371   0.7362   0.7070
  -2.000   0.0947   0.04071   0.03063  -0.0362   0.7228   0.7221
  -1.750   0.1000   0.04077   0.03067  -0.0339   0.7118   0.7325
  -1.500   0.1333   0.04052   0.03033  -0.0339   0.7059   0.7380
  -1.250   0.1479   0.04062   0.03039  -0.0322   0.6969   0.7460
  -1.000   0.1622   0.04055   0.03027  -0.0308   0.6881   0.7545
  -0.750   0.1960   0.04020   0.02984  -0.0310   0.6829   0.7599
  -0.500   0.2036   0.04055   0.03018  -0.0286   0.6725   0.7678
  -0.250   0.2227   0.04040   0.02998  -0.0277   0.6649   0.7753
   0.000   0.2572   0.03995   0.02945  -0.0282   0.6602   0.7800
   0.250   0.2595   0.04052   0.03005  -0.0252   0.6487   0.7866
   0.500   0.2824   0.04026   0.02972  -0.0252   0.6419   0.7934
   0.750   0.3182   0.03972   0.02910  -0.0258   0.6376   0.7973
   1.000   0.3158   0.04054   0.02999  -0.0222   0.6250   0.8028
   1.250   0.3455   0.04015   0.02953  -0.0226   0.6191   0.8079
   1.500   0.3615   0.04034   0.02971  -0.0218   0.6109   0.8135
   1.750   0.3751   0.04058   0.02997  -0.0200   0.6015   0.8176
   2.000   0.4100   0.04002   0.02935  -0.0206   0.5964   0.8217
   2.250   0.4124   0.04084   0.03021  -0.0182   0.5853   0.8271
   2.500   0.4399   0.04069   0.03002  -0.0187   0.5781   0.8319
   2.750   0.4780   0.03994   0.02922  -0.0194   0.5738   0.8351
   3.000   0.4688   0.04125   0.03063  -0.0156   0.5608   0.8400
   3.250   0.5034   0.04075   0.03009  -0.0164   0.5552   0.8440
   3.500   0.5150   0.04145   0.03082  -0.0154   0.5456   0.8489
   3.750   0.5327   0.04166   0.03104  -0.0144   0.5369   0.8527
   4.000   0.5746   0.04076   0.03009  -0.0156   0.5323   0.8557
   4.250   0.5624   0.04249   0.03193  -0.0121   0.5191   0.8606
   4.500   0.6032   0.04178   0.03119  -0.0136   0.5132   0.8645
   4.750   0.6014   0.04302   0.03250  -0.0111   0.5019   0.8690
   5.000   0.6286   0.04272   0.03220  -0.0108   0.4941   0.8726
   5.250   0.6776   0.04148   0.03088  -0.0127   0.4887   0.8756
   5.500   0.6648   0.04355   0.03309  -0.0099   0.4749   0.8802
   5.750   0.7184   0.04184   0.03129  -0.0118   0.4696   0.8834
   6.000   0.6996   0.04435   0.03395  -0.0085   0.4555   0.8885
   6.250   0.7478   0.04267   0.03219  -0.0095   0.4499   0.8924
   6.500   0.7378   0.04534   0.03501  -0.0081   0.4358   0.8973
   6.750   0.7827   0.04365   0.03325  -0.0086   0.4300   0.9006
   7.000   0.7707   0.04644   0.03618  -0.0070   0.4162   0.9051
   7.250   0.8179   0.04466   0.03432  -0.0077   0.4100   0.9090
   7.500   0.8062   0.04765   0.03747  -0.0065   0.3963   0.9138
   7.750   0.8512   0.04568   0.03539  -0.0065   0.3901   0.9185
   8.000   0.8374   0.04902   0.03890  -0.0055   0.3764   0.9239
   8.250   0.8755   0.04768   0.03748  -0.0055   0.3692   0.9286
   8.500   0.8670   0.05062   0.04057  -0.0048   0.3564   0.9338
   8.750   0.8861   0.05124   0.04119  -0.0047   0.3470   0.9386
   9.000   0.8951   0.05264   0.04264  -0.0044   0.3365   0.9440
   9.250   0.9000   0.05463   0.04471  -0.0043   0.3262   0.9499
   9.500   0.9185   0.05514   0.04522  -0.0041   0.3171   0.9565
   9.750   0.9148   0.05817   0.04836  -0.0042   0.3065   0.9634
  10.000   0.9380   0.05822   0.04838  -0.0042   0.2986   0.9716
  10.250   0.9280   0.06211   0.05240  -0.0048   0.2884   0.9813
  10.500   0.9474   0.06227   0.05256  -0.0048   0.2809   1.0000
  10.750   0.9401   0.06673   0.05715  -0.0062   0.2714   1.0000
  11.000   0.9610   0.06779   0.05819  -0.0071   0.2642   1.0000
  11.250   0.9652   0.07098   0.06144  -0.0084   0.2566   1.0000
  11.500   0.9607   0.07532   0.06589  -0.0100   0.2483   1.0000
  11.750   1.0125   0.07244   0.06284  -0.0098   0.2442   1.0000
  12.000   0.9366   0.08671   0.07753  -0.0142   0.2327   1.0000
  12.250   0.9804   0.08446   0.07518  -0.0140   0.2292   1.0000
  12.500   0.8936   0.10207   0.09312  -0.0204   0.2164   1.0000
  12.750   0.9277   0.10095   0.09198  -0.0205   0.2135   1.0000
  13.000   0.9779   0.09733   0.08828  -0.0196   0.2117   1.0000
  13.250   0.8789   0.11873   0.10998  -0.0285   0.1981   1.0000
  13.500   0.9138   0.11715   0.10838  -0.0283   0.1964   1.0000
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