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LWK 79-100 (lwk79100-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: LWK 79-100 (lwk79100-il)
Reynolds number: 500,000
Max Cl/Cd: 59.49 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-lwk79100-il-500000.txt
Download as CSV file: xf-lwk79100-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.250  -0.5905   0.15400   0.15190   0.0378   1.0000   0.0264
 -14.000  -0.5914   0.15034   0.14824   0.0355   1.0000   0.0273
 -13.750  -1.0424   0.06379   0.06046  -0.0148   1.0000   0.0134
 -12.750  -1.1154   0.04172   0.03758  -0.0255   1.0000   0.0136
 -12.500  -1.1271   0.03812   0.03378  -0.0256   1.0000   0.0137
 -12.250  -1.1350   0.03538   0.03086  -0.0244   1.0000   0.0139
 -12.000  -1.1387   0.03333   0.02868  -0.0221   1.0000   0.0141
 -11.750  -1.1351   0.03171   0.02694  -0.0202   1.0000   0.0144
 -11.500  -1.1249   0.03040   0.02554  -0.0188   1.0000   0.0147
 -11.250  -1.1127   0.02908   0.02410  -0.0176   1.0000   0.0151
 -11.000  -1.0991   0.02774   0.02263  -0.0164   1.0000   0.0156
 -10.750  -1.0839   0.02642   0.02116  -0.0153   1.0000   0.0162
 -10.500  -1.0663   0.02536   0.01997  -0.0143   1.0000   0.0168
 -10.250  -1.0472   0.02444   0.01890  -0.0134   1.0000   0.0174
 -10.000  -1.0328   0.02252   0.01682  -0.0122   1.0000   0.0183
  -9.750  -1.0142   0.02138   0.01562  -0.0113   1.0000   0.0193
  -9.500  -0.9929   0.02062   0.01482  -0.0106   1.0000   0.0203
  -9.250  -0.9712   0.01984   0.01395  -0.0098   1.0000   0.0214
  -9.000  -0.9487   0.01914   0.01315  -0.0091   1.0000   0.0225
  -8.750  -0.9294   0.01787   0.01177  -0.0081   1.0000   0.0240
  -8.500  -0.9077   0.01703   0.01091  -0.0074   1.0000   0.0257
  -8.250  -0.8836   0.01657   0.01042  -0.0069   1.0000   0.0277
  -8.000  -0.8590   0.01615   0.00992  -0.0064   1.0000   0.0294
  -7.750  -0.8380   0.01510   0.00881  -0.0055   1.0000   0.0317
  -7.500  -0.8144   0.01449   0.00818  -0.0049   1.0000   0.0340
  -7.250  -0.7897   0.01403   0.00768  -0.0044   1.0000   0.0364
  -7.000  -0.7641   0.01373   0.00732  -0.0040   1.0000   0.0384
  -6.750  -0.7419   0.01285   0.00644  -0.0032   1.0000   0.0427
  -6.500  -0.7168   0.01245   0.00601  -0.0027   1.0000   0.0463
  -6.250  -0.6921   0.01195   0.00546  -0.0021   1.0000   0.0503
  -6.000  -0.6675   0.01146   0.00500  -0.0016   1.0000   0.0570
  -5.750  -0.6428   0.01096   0.00454  -0.0010   1.0000   0.0666
  -5.500  -0.6181   0.01049   0.00414  -0.0004   1.0000   0.0823
  -5.250  -0.5935   0.01000   0.00377   0.0001   1.0000   0.1068
  -5.000  -0.5688   0.00956   0.00347   0.0006   1.0000   0.1356
  -4.750  -0.5440   0.00916   0.00321   0.0011   1.0000   0.1659
  -4.250  -0.4945   0.00838   0.00273   0.0021   1.0000   0.2341
  -4.000  -0.4702   0.00797   0.00252   0.0027   1.0000   0.2781
  -3.750  -0.4339   0.00755   0.00233   0.0006   0.9835   0.3357
  -3.500  -0.3822   0.00719   0.00214  -0.0046   0.9151   0.3987
  -3.250  -0.3540   0.00717   0.00201  -0.0043   0.8359   0.4419
  -3.000  -0.3291   0.00715   0.00195  -0.0035   0.8011   0.4786
  -2.750  -0.3029   0.00715   0.00190  -0.0030   0.7794   0.5069
  -2.500  -0.2762   0.00714   0.00188  -0.0026   0.7631   0.5301
  -2.250  -0.2489   0.00716   0.00185  -0.0022   0.7497   0.5498
  -2.000  -0.2214   0.00717   0.00183  -0.0020   0.7381   0.5664
  -1.750  -0.1940   0.00720   0.00182  -0.0017   0.7279   0.5814
  -1.500  -0.1663   0.00721   0.00180  -0.0014   0.7180   0.5946
  -1.250  -0.1386   0.00721   0.00180  -0.0012   0.7088   0.6064
  -1.000  -0.1110   0.00724   0.00179  -0.0009   0.7002   0.6180
  -0.750  -0.0831   0.00724   0.00179  -0.0007   0.6907   0.6294
  -0.500  -0.0553   0.00726   0.00178  -0.0005   0.6803   0.6398
  -0.250  -0.0279   0.00727   0.00178  -0.0002   0.6697   0.6492
   0.000   0.0000   0.00725   0.00177   0.0000   0.6594   0.6594
   0.250   0.0279   0.00727   0.00178   0.0002   0.6493   0.6697
   0.500   0.0553   0.00726   0.00178   0.0005   0.6398   0.6803
   0.750   0.0831   0.00724   0.00179   0.0007   0.6293   0.6907
   1.250   0.1386   0.00721   0.00180   0.0012   0.6065   0.7088
   1.500   0.1663   0.00721   0.00180   0.0014   0.5946   0.7180
   1.750   0.1939   0.00720   0.00181   0.0017   0.5813   0.7279
   2.000   0.2215   0.00717   0.00183   0.0020   0.5664   0.7382
   2.250   0.2489   0.00716   0.00185   0.0022   0.5498   0.7497
   2.500   0.2762   0.00714   0.00188   0.0026   0.5301   0.7631
   2.750   0.3029   0.00715   0.00190   0.0030   0.5069   0.7793
   3.000   0.3291   0.00715   0.00195   0.0035   0.4786   0.8011
   3.250   0.3540   0.00717   0.00201   0.0043   0.4419   0.8357
   3.500   0.3821   0.00719   0.00214   0.0046   0.3987   0.9148
   3.750   0.4340   0.00755   0.00233  -0.0006   0.3354   0.9836
   4.000   0.4701   0.00797   0.00252  -0.0027   0.2780   1.0000
   4.250   0.4944   0.00838   0.00273  -0.0021   0.2339   1.0000
   4.750   0.5439   0.00916   0.00321  -0.0011   0.1659   1.0000
   5.000   0.5687   0.00956   0.00347  -0.0006   0.1357   1.0000
   5.250   0.5935   0.01000   0.00377  -0.0001   0.1068   1.0000
   5.500   0.6180   0.01048   0.00414   0.0005   0.0823   1.0000
   5.750   0.6428   0.01096   0.00454   0.0010   0.0666   1.0000
   6.000   0.6675   0.01145   0.00500   0.0016   0.0569   1.0000
   6.250   0.6921   0.01195   0.00547   0.0021   0.0503   1.0000
   6.500   0.7168   0.01245   0.00601   0.0027   0.0463   1.0000
   6.750   0.7419   0.01285   0.00644   0.0032   0.0427   1.0000
   7.000   0.7641   0.01374   0.00734   0.0040   0.0383   1.0000
   7.250   0.7897   0.01405   0.00769   0.0044   0.0365   1.0000
   7.500   0.8145   0.01449   0.00818   0.0049   0.0340   1.0000
   7.750   0.8380   0.01510   0.00881   0.0055   0.0316   1.0000
   8.000   0.8590   0.01616   0.00993   0.0064   0.0294   1.0000
   8.250   0.8838   0.01656   0.01040   0.0069   0.0276   1.0000
   8.500   0.9079   0.01703   0.01091   0.0074   0.0257   1.0000
   8.750   0.9294   0.01790   0.01180   0.0081   0.0239   1.0000
   9.000   0.9488   0.01917   0.01318   0.0091   0.0225   1.0000
   9.250   0.9714   0.01986   0.01397   0.0098   0.0214   1.0000
   9.500   0.9933   0.02060   0.01479   0.0105   0.0202   1.0000
   9.750   1.0144   0.02138   0.01562   0.0112   0.0193   1.0000
  10.000   1.0333   0.02248   0.01678   0.0121   0.0184   1.0000
  10.250   1.0473   0.02450   0.01897   0.0134   0.0174   1.0000
  10.500   1.0673   0.02524   0.01985   0.0142   0.0168   1.0000
  10.750   1.0845   0.02639   0.02113   0.0152   0.0161   1.0000
  11.000   1.0997   0.02771   0.02260   0.0163   0.0156   1.0000
  11.250   1.1135   0.02905   0.02407   0.0175   0.0151   1.0000
  11.500   1.1259   0.03034   0.02547   0.0187   0.0147   1.0000
  11.750   1.1360   0.03169   0.02691   0.0200   0.0143   1.0000
  12.000   1.1399   0.03330   0.02865   0.0220   0.0141   1.0000
  12.250   1.1348   0.03552   0.03099   0.0242   0.0138   1.0000
  12.500   1.1280   0.03815   0.03380   0.0254   0.0137   1.0000
  12.750   1.1131   0.04215   0.03802   0.0253   0.0136   1.0000
  13.000   1.0987   0.04652   0.04260   0.0241   0.0135   1.0000
  13.750   0.6181   0.14041   0.13829  -0.0305   0.0206   1.0000
  14.000   0.6094   0.14477   0.14266  -0.0330   0.0220   1.0000
  14.250   1.0163   0.07629   0.07325   0.0061   0.0135   1.0000
  14.500   0.9903   0.08568   0.08282  -0.0004   0.0135   1.0000
  14.750   0.9727   0.09409   0.09136  -0.0061   0.0136   1.0000
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