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NASA/LANGLEY LS(1)-0417 (GA(W)-1) AIRFOIL (ls417-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NASA/LANGLEY LS(1)-0417 (GA(W)-1) AIRFOIL (ls417-il)
Reynolds number: 100,000
Max Cl/Cd: 42.91 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ls417-il-100000.txt
Download as CSV file: xf-ls417-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA/LANGLEY LS(1)-0417 (GA(W)-1) 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.5270   0.08967   0.08518  -0.0484   1.0000   0.0930
 -10.250  -0.5795   0.07963   0.07505  -0.0507   1.0000   0.0866
 -10.000  -0.6830   0.07040   0.06555  -0.0494   1.0000   0.0839
  -9.750  -0.8036   0.07094   0.06548  -0.0453   1.0000   0.0838
  -9.500  -0.8620   0.06150   0.05488  -0.0425   1.0000   0.0741
  -9.250  -0.8437   0.05794   0.05124  -0.0432   0.9979   0.0731
  -9.000  -0.8296   0.05417   0.04720  -0.0439   0.9957   0.0721
  -8.750  -0.8137   0.05033   0.04293  -0.0449   0.9936   0.0711
  -8.500  -0.7944   0.04708   0.03923  -0.0459   0.9912   0.0712
  -8.250  -0.7721   0.04441   0.03610  -0.0468   0.9883   0.0722
  -8.000  -0.7462   0.04204   0.03324  -0.0479   0.9856   0.0731
  -7.750  -0.7182   0.04004   0.03080  -0.0490   0.9835   0.0739
  -7.500  -0.6891   0.03824   0.02893  -0.0500   0.9817   0.0751
  -7.250  -0.6622   0.03701   0.02767  -0.0504   0.9799   0.0768
  -7.000  -0.6384   0.03589   0.02645  -0.0501   0.9774   0.0789
  -6.750  -0.6111   0.03493   0.02524  -0.0505   0.9745   0.0823
  -6.500  -0.5838   0.03402   0.02450  -0.0510   0.9720   0.0865
  -6.250  -0.5549   0.03329   0.02364  -0.0515   0.9701   0.0916
  -6.000  -0.5248   0.03251   0.02305  -0.0525   0.9681   0.0978
  -5.750  -0.4981   0.03180   0.02246  -0.0529   0.9656   0.1071
  -5.500  -0.4747   0.03100   0.02180  -0.0529   0.9626   0.1212
  -5.250  -0.4472   0.02998   0.02106  -0.0540   0.9603   0.1478
  -5.000  -0.4125   0.02841   0.02026  -0.0572   0.9584   0.2283
  -4.750  -0.3730   0.02680   0.02050  -0.0612   0.9562   0.4941
  -4.500  -0.3518   0.02825   0.02231  -0.0581   0.9530   0.5956
  -4.250  -0.3326   0.02950   0.02348  -0.0557   0.9498   0.6388
  -4.000  -0.3194   0.03056   0.02445  -0.0524   0.9473   0.6636
  -3.750  -0.3036   0.03159   0.02541  -0.0494   0.9437   0.6824
  -3.500  -0.2913   0.03277   0.02657  -0.0448   0.9404   0.6945
  -3.250  -0.2742   0.03396   0.02769  -0.0415   0.9377   0.7104
  -3.000  -0.2558   0.03525   0.02892  -0.0381   0.9340   0.7277
  -2.750  -0.2504   0.03584   0.02948  -0.0334   0.9301   0.7431
  -2.500  -0.2376   0.03648   0.03006  -0.0301   0.9264   0.7586
  -2.250  -0.2182   0.03715   0.03066  -0.0278   0.9220   0.7744
  -2.000  -0.1915   0.03800   0.03143  -0.0265   0.9179   0.7910
  -1.750  -0.1908   0.03824   0.03167  -0.0206   0.9126   0.8035
  -1.500  -0.1821   0.03844   0.03184  -0.0165   0.9073   0.8184
  -1.250  -0.1605   0.03869   0.03202  -0.0149   0.9020   0.8328
  -1.000  -0.1268   0.03907   0.03230  -0.0163   0.8959   0.8442
  -0.750  -0.1191   0.03891   0.03211  -0.0133   0.8889   0.8529
  -0.500  -0.0881   0.03904   0.03216  -0.0144   0.8824   0.8617
  -0.250  -0.0554   0.03932   0.03237  -0.0154   0.8759   0.8705
   0.000  -0.0450   0.03919   0.03222  -0.0132   0.8673   0.8786
   0.250  -0.0097   0.03935   0.03232  -0.0148   0.8608   0.8874
   0.500   0.0095   0.03941   0.03235  -0.0139   0.8523   0.8946
   0.750   0.0346   0.03947   0.03237  -0.0141   0.8439   0.9015
   1.000   0.0822   0.03968   0.03252  -0.0177   0.8384   0.9068
   1.250   0.0886   0.03963   0.03249  -0.0152   0.8263   0.9123
   1.500   0.1342   0.03971   0.03253  -0.0185   0.8196   0.9170
   1.750   0.1512   0.03980   0.03262  -0.0177   0.8074   0.9214
   2.000   0.1949   0.03962   0.03242  -0.0203   0.8000   0.9251
   2.250   0.2148   0.03977   0.03258  -0.0199   0.7876   0.9293
   2.500   0.2614   0.03955   0.03236  -0.0230   0.7804   0.9325
   2.750   0.2815   0.03958   0.03241  -0.0225   0.7673   0.9359
   3.000   0.3302   0.03892   0.03175  -0.0251   0.7603   0.9391
   3.250   0.3524   0.03892   0.03178  -0.0249   0.7464   0.9429
   3.500   0.4046   0.03808   0.03096  -0.0280   0.7405   0.9451
   3.750   0.4274   0.03791   0.03084  -0.0276   0.7262   0.9485
   4.000   0.4864   0.03611   0.02908  -0.0305   0.7209   0.9513
   4.250   0.5118   0.03566   0.02868  -0.0301   0.7060   0.9550
   4.500   0.5699   0.03374   0.02682  -0.0329   0.7021   0.9570
   4.750   0.5941   0.03334   0.02650  -0.0324   0.6873   0.9604
   5.000   0.6522   0.03091   0.02414  -0.0348   0.6837   0.9630
   5.250   0.6804   0.02996   0.02328  -0.0342   0.6691   0.9678
   5.500   0.7446   0.02691   0.02029  -0.0369   0.6646   0.9703
   5.750   0.7771   0.02568   0.01916  -0.0368   0.6477   0.9743
   6.000   0.8139   0.02429   0.01785  -0.0371   0.6290   0.9784
   6.250   0.8372   0.02372   0.01735  -0.0362   0.6008   0.9839
   6.500   0.8761   0.02248   0.01606  -0.0369   0.5625   0.9886
   6.750   0.9179   0.02139   0.01459  -0.0377   0.4995   0.9935
   7.000   0.9314   0.02173   0.01444  -0.0354   0.4336   1.0000
   7.250   0.9414   0.02283   0.01508  -0.0334   0.3773   1.0000
   7.500   0.9531   0.02411   0.01596  -0.0320   0.3327   1.0000
   7.750   0.9688   0.02540   0.01694  -0.0314   0.2982   1.0000
   8.000   0.9891   0.02664   0.01787  -0.0313   0.2719   1.0000
   8.250   1.0120   0.02782   0.01887  -0.0317   0.2505   1.0000
   8.500   1.0380   0.02896   0.01984  -0.0324   0.2332   1.0000
   8.750   1.0660   0.03007   0.02083  -0.0334   0.2189   1.0000
   9.000   1.0935   0.03118   0.02196  -0.0344   0.2068   1.0000
   9.250   1.1261   0.03236   0.02304  -0.0359   0.1966   1.0000
   9.500   1.1561   0.03348   0.02414  -0.0372   0.1878   1.0000
   9.750   1.1902   0.03480   0.02545  -0.0390   0.1800   1.0000
  10.000   1.2188   0.03599   0.02669  -0.0401   0.1730   1.0000
  10.250   1.2583   0.03750   0.02810  -0.0427   0.1665   1.0000
  10.500   1.2793   0.03887   0.02968  -0.0428   0.1609   1.0000
  10.750   1.3142   0.04023   0.03094  -0.0448   0.1551   1.0000
  11.000   1.3387   0.04202   0.03290  -0.0455   0.1502   1.0000
  11.250   1.3562   0.04357   0.03465  -0.0452   0.1457   1.0000
  11.500   1.3886   0.04507   0.03605  -0.0469   0.1407   1.0000
  11.750   1.4057   0.04719   0.03840  -0.0467   0.1370   1.0000
  12.000   1.4137   0.04907   0.04056  -0.0453   0.1334   1.0000
  12.250   1.4314   0.05072   0.04231  -0.0452   0.1296   1.0000
  12.500   1.4634   0.05300   0.04451  -0.0470   0.1255   1.0000
  12.750   1.4526   0.05539   0.04732  -0.0436   0.1235   1.0000
  13.000   1.4477   0.05795   0.05019  -0.0413   0.1210   1.0000
  13.250   1.4561   0.06007   0.05244  -0.0404   0.1180   1.0000
  13.500   1.4977   0.06204   0.05416  -0.0429   0.1141   1.0000
  13.750   1.4715   0.06529   0.05786  -0.0390   0.1131   1.0000
  14.000   1.4452   0.06919   0.06216  -0.0359   0.1121   1.0000
  14.250   1.4176   0.07366   0.06700  -0.0335   0.1111   1.0000
  14.500   1.3869   0.07881   0.07249  -0.0319   0.1103   1.0000
  14.750   1.3499   0.08500   0.07902  -0.0311   0.1099   1.0000
  15.000   1.3011   0.09309   0.08747  -0.0317   0.1101   1.0000
  15.250   1.2343   0.10475   0.09950  -0.0351   0.1112   1.0000
  15.500   1.1496   0.12265   0.11772  -0.0441   0.1130   1.0000
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