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LWK 80-080 (lwk80080-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: LWK 80-080 (lwk80080-il)
Reynolds number: 500,000
Max Cl/Cd: 47.24 at α=2.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-lwk80080-il-500000.txt
Download as CSV file: xf-lwk80080-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: LWK 80-080                                      
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.6927   0.07669   0.07458  -0.0146   1.0000   0.0144
  -9.250  -0.7037   0.07128   0.06912  -0.0190   1.0000   0.0146
  -9.000  -0.7197   0.06580   0.06354  -0.0213   1.0000   0.0146
  -8.750  -0.7250   0.06293   0.06061  -0.0209   1.0000   0.0151
  -8.500  -0.7263   0.05979   0.05739  -0.0208   1.0000   0.0158
  -8.250  -0.7361   0.05257   0.04989  -0.0204   1.0000   0.0149
  -7.500  -0.7323   0.03624   0.03243  -0.0137   1.0000   0.0136
  -7.250  -0.7120   0.03546   0.03154  -0.0126   1.0000   0.0132
  -7.000  -0.7128   0.02924   0.02475  -0.0091   1.0000   0.0135
  -6.750  -0.7010   0.02576   0.02088  -0.0067   1.0000   0.0135
  -6.500  -0.6812   0.02448   0.01944  -0.0053   1.0000   0.0132
  -6.250  -0.6653   0.02174   0.01637  -0.0032   1.0000   0.0132
  -6.000  -0.6526   0.01725   0.01138  -0.0004   1.0000   0.0140
  -5.750  -0.6357   0.01565   0.00964   0.0016   1.0000   0.0147
  -5.250  -0.5867   0.01396   0.00779   0.0021   0.9930   0.0170
  -5.000  -0.5546   0.01277   0.00648   0.0010   0.9878   0.0175
  -4.750  -0.5219   0.01186   0.00547  -0.0001   0.9823   0.0202
  -4.500  -0.4907   0.01088   0.00437  -0.0011   0.9758   0.0247
  -4.250  -0.4560   0.01036   0.00382  -0.0027   0.9711   0.0335
  -4.000  -0.4203   0.00981   0.00330  -0.0048   0.9670   0.0514
  -3.750  -0.3863   0.00933   0.00293  -0.0064   0.9612   0.0799
  -3.500  -0.3524   0.00860   0.00258  -0.0084   0.9561   0.1648
  -3.250  -0.3258   0.00761   0.00224  -0.0090   0.9480   0.3285
  -3.000  -0.3047   0.00643   0.00192  -0.0083   0.9398   0.5514
  -2.750  -0.2845   0.00602   0.00191  -0.0066   0.9311   0.6758
  -2.500  -0.2576   0.00596   0.00193  -0.0063   0.9251   0.7249
  -2.250  -0.2327   0.00597   0.00197  -0.0054   0.9183   0.7559
  -2.000  -0.2048   0.00602   0.00197  -0.0053   0.9132   0.7755
  -1.750  -0.1801   0.00605   0.00199  -0.0045   0.9067   0.7894
  -1.500  -0.1536   0.00609   0.00199  -0.0040   0.9015   0.8025
  -1.250  -0.1278   0.00613   0.00203  -0.0035   0.8963   0.8148
  -1.000  -0.1033   0.00619   0.00210  -0.0025   0.8906   0.8298
  -0.750  -0.0767   0.00624   0.00215  -0.0020   0.8862   0.8420
  -0.500  -0.0514   0.00625   0.00219  -0.0013   0.8807   0.8509
  -0.250  -0.0259   0.00628   0.00221  -0.0006   0.8750   0.8607
   0.000  -0.0001   0.00629   0.00223   0.0000   0.8686   0.8688
   0.250   0.0259   0.00628   0.00221   0.0006   0.8606   0.8750
   0.500   0.0514   0.00625   0.00219   0.0013   0.8510   0.8807
   0.750   0.0766   0.00624   0.00215   0.0020   0.8417   0.8862
   1.000   0.1030   0.00618   0.00209   0.0026   0.8290   0.8907
   1.250   0.1279   0.00614   0.00204   0.0034   0.8152   0.8963
   1.500   0.1536   0.00609   0.00199   0.0041   0.8026   0.9014
   1.750   0.1801   0.00605   0.00198   0.0045   0.7890   0.9067
   2.000   0.2048   0.00602   0.00198   0.0053   0.7755   0.9131
   2.250   0.2329   0.00597   0.00197   0.0054   0.7572   0.9182
   2.500   0.2570   0.00596   0.00191   0.0065   0.7201   0.9252
   2.750   0.2844   0.00602   0.00190   0.0067   0.6731   0.9312
   3.000   0.3039   0.00647   0.00193   0.0085   0.5423   0.9401
   3.250   0.3258   0.00762   0.00224   0.0090   0.3266   0.9480
   3.500   0.3515   0.00871   0.00259   0.0085   0.1464   0.9562
   3.750   0.3862   0.00934   0.00293   0.0065   0.0787   0.9611
   4.000   0.4203   0.00979   0.00326   0.0047   0.0499   0.9670
   4.250   0.4560   0.01037   0.00382   0.0027   0.0321   0.9711
   4.500   0.4893   0.01123   0.00475   0.0014   0.0212   0.9765
   4.750   0.5222   0.01189   0.00550   0.0002   0.0182   0.9824
   5.000   0.5546   0.01281   0.00652  -0.0010   0.0170   0.9880
   5.250   0.5867   0.01400   0.00783  -0.0021   0.0167   0.9931
   5.750   0.6351   0.01579   0.00979  -0.0015   0.0143   1.0000
   6.000   0.6514   0.01780   0.01198   0.0007   0.0138   1.0000
   6.250   0.6676   0.02085   0.01537   0.0028   0.0134   1.0000
   6.500   0.6816   0.02440   0.01934   0.0053   0.0133   1.0000
   6.750   0.7009   0.02590   0.02104   0.0068   0.0135   1.0000
   7.500   0.6956   0.04752   0.04431   0.0170   0.0214   1.0000
   7.750   0.7243   0.04701   0.04406   0.0184   0.0173   1.0000
   8.000   0.7267   0.05154   0.04881   0.0197   0.0172   1.0000
   8.250   0.7328   0.05401   0.05140   0.0204   0.0155   1.0000
   8.500   0.7282   0.05921   0.05679   0.0208   0.0154   1.0000
   8.750   0.7221   0.06409   0.06180   0.0205   0.0155   1.0000
   9.000   0.7001   0.07118   0.06902   0.0185   0.0167   1.0000
   9.250   0.6849   0.07783   0.07573   0.0127   0.0168   1.0000
   9.500   0.6862   0.08081   0.07871   0.0096   0.0148   1.0000
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