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LWK 79-100 (lwk79100-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: LWK 79-100 (lwk79100-il)
Reynolds number: 100,000
Max Cl/Cd: 37.36 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-lwk79100-il-100000.txt
Download as CSV file: xf-lwk79100-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: LWK 79-100                                      
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.5968   0.11537   0.11071   0.0127   1.0000   0.1537
 -10.500  -0.7428   0.09516   0.09025   0.0003   1.0000   0.0976
 -10.250  -0.8268   0.07223   0.06716  -0.0158   1.0000   0.0705
 -10.000  -0.8428   0.06736   0.06221  -0.0168   1.0000   0.0695
  -9.750  -0.8601   0.06235   0.05703  -0.0172   1.0000   0.0685
  -9.500  -0.8734   0.05716   0.05156  -0.0173   1.0000   0.0678
  -9.250  -0.8806   0.05225   0.04628  -0.0170   1.0000   0.0678
  -9.000  -0.8812   0.04780   0.04136  -0.0162   1.0000   0.0686
  -8.750  -0.8767   0.04365   0.03666  -0.0152   1.0000   0.0698
  -8.500  -0.8666   0.03992   0.03234  -0.0140   1.0000   0.0707
  -8.250  -0.8532   0.03644   0.02830  -0.0129   1.0000   0.0724
  -8.000  -0.8331   0.03396   0.02587  -0.0125   1.0000   0.0768
  -7.750  -0.8126   0.03173   0.02332  -0.0116   1.0000   0.0807
  -7.500  -0.7913   0.02970   0.02073  -0.0105   1.0000   0.0844
  -7.250  -0.7686   0.02749   0.01860  -0.0101   1.0000   0.0903
  -7.000  -0.7446   0.02586   0.01671  -0.0093   1.0000   0.0964
  -6.750  -0.7208   0.02410   0.01500  -0.0087   1.0000   0.1037
  -6.500  -0.6968   0.02270   0.01348  -0.0079   1.0000   0.1135
  -6.250  -0.6728   0.02140   0.01215  -0.0071   1.0000   0.1252
  -6.000  -0.6503   0.02003   0.01097  -0.0063   1.0000   0.1424
  -5.750  -0.6280   0.01880   0.00986  -0.0054   1.0000   0.1682
  -5.500  -0.6074   0.01749   0.00890  -0.0044   1.0000   0.2061
  -5.250  -0.5872   0.01626   0.00803  -0.0033   1.0000   0.2599
  -5.000  -0.5668   0.01529   0.00745  -0.0022   1.0000   0.3264
  -4.750  -0.5459   0.01461   0.00714  -0.0009   1.0000   0.3965
  -4.500  -0.5241   0.01427   0.00705   0.0005   1.0000   0.4596
  -4.250  -0.5015   0.01419   0.00709   0.0021   1.0000   0.5095
  -4.000  -0.4784   0.01423   0.00716   0.0035   1.0000   0.5500
  -3.750  -0.4553   0.01427   0.00724   0.0051   1.0000   0.5821
  -3.500  -0.4323   0.01428   0.00725   0.0066   1.0000   0.6106
  -3.250  -0.4096   0.01423   0.00726   0.0082   1.0000   0.6339
  -3.000  -0.3874   0.01413   0.00718   0.0097   1.0000   0.6574
  -2.750  -0.3660   0.01400   0.00711   0.0113   1.0000   0.6780
  -2.500  -0.3460   0.01384   0.00698   0.0129   1.0000   0.6992
  -2.250  -0.3293   0.01369   0.00690   0.0148   1.0000   0.7179
  -2.000  -0.3182   0.01361   0.00689   0.0173   1.0000   0.7358
  -1.750  -0.3043   0.01359   0.00690   0.0190   0.9983   0.7546
  -1.500  -0.2561   0.01360   0.00690   0.0148   0.9810   0.7770
  -1.250  -0.2106   0.01354   0.00688   0.0115   0.9650   0.7979
  -1.000  -0.1648   0.01347   0.00682   0.0082   0.9506   0.8196
  -0.750  -0.1217   0.01339   0.00679   0.0058   0.9360   0.8388
  -0.500  -0.0800   0.01332   0.00674   0.0036   0.9210   0.8568
  -0.250  -0.0395   0.01327   0.00670   0.0017   0.9056   0.8736
   0.000   0.0000   0.01325   0.00668   0.0000   0.8898   0.8898
   0.250   0.0396   0.01327   0.00670  -0.0017   0.8736   0.9056
   0.500   0.0800   0.01332   0.00674  -0.0036   0.8568   0.9210
   0.750   0.1217   0.01339   0.00678  -0.0058   0.8387   0.9360
   1.000   0.1648   0.01347   0.00682  -0.0082   0.8196   0.9506
   1.250   0.2106   0.01354   0.00688  -0.0115   0.7979   0.9651
   1.500   0.2562   0.01359   0.00690  -0.0148   0.7772   0.9811
   1.750   0.3044   0.01359   0.00690  -0.0190   0.7546   0.9984
   2.000   0.3181   0.01361   0.00689  -0.0173   0.7358   1.0000
   2.250   0.3292   0.01369   0.00690  -0.0148   0.7179   1.0000
   2.500   0.3459   0.01384   0.00698  -0.0128   0.6992   1.0000
   2.750   0.3659   0.01400   0.00711  -0.0113   0.6780   1.0000
   3.000   0.3873   0.01413   0.00718  -0.0096   0.6574   1.0000
   3.250   0.4095   0.01423   0.00726  -0.0082   0.6339   1.0000
   3.500   0.4322   0.01428   0.00725  -0.0065   0.6105   1.0000
   3.750   0.4552   0.01427   0.00724  -0.0051   0.5821   1.0000
   4.000   0.4784   0.01423   0.00716  -0.0035   0.5501   1.0000
   4.250   0.5014   0.01419   0.00709  -0.0021   0.5095   1.0000
   4.500   0.5240   0.01427   0.00705  -0.0005   0.4595   1.0000
   4.750   0.5458   0.01461   0.00714   0.0009   0.3965   1.0000
   5.000   0.5667   0.01529   0.00745   0.0022   0.3264   1.0000
   5.250   0.5872   0.01626   0.00803   0.0033   0.2599   1.0000
   5.500   0.6074   0.01749   0.00890   0.0044   0.2062   1.0000
   5.750   0.6280   0.01880   0.00986   0.0054   0.1682   1.0000
   6.000   0.6504   0.02003   0.01097   0.0063   0.1423   1.0000
   6.250   0.6728   0.02141   0.01215   0.0071   0.1251   1.0000
   6.500   0.6969   0.02270   0.01348   0.0079   0.1134   1.0000
   6.750   0.7209   0.02410   0.01500   0.0087   0.1035   1.0000
   7.000   0.7447   0.02586   0.01672   0.0093   0.0963   1.0000
   7.250   0.7687   0.02750   0.01861   0.0101   0.0903   1.0000
   7.500   0.7914   0.02969   0.02073   0.0105   0.0844   1.0000
   7.750   0.8127   0.03174   0.02333   0.0116   0.0807   1.0000
   8.000   0.8332   0.03397   0.02588   0.0125   0.0768   1.0000
   8.250   0.8533   0.03648   0.02833   0.0129   0.0724   1.0000
   8.500   0.8668   0.03993   0.03235   0.0140   0.0707   1.0000
   8.750   0.8768   0.04369   0.03670   0.0152   0.0697   1.0000
   9.000   0.8816   0.04782   0.04138   0.0162   0.0687   1.0000
   9.250   0.8807   0.05233   0.04635   0.0169   0.0680   1.0000
   9.500   0.8736   0.05720   0.05160   0.0173   0.0678   1.0000
   9.750   0.8608   0.06238   0.05706   0.0171   0.0686   1.0000
  10.000   0.8442   0.06735   0.06220   0.0167   0.0696   1.0000
  10.250   0.8275   0.07229   0.06721   0.0157   0.0705   1.0000
  10.500   0.7530   0.09378   0.08893   0.0014   0.0986   1.0000
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