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LWK 80-120/K25 (lwk80120k25-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: LWK 80-120/K25 (lwk80120k25-il)
Reynolds number: 100,000
Max Cl/Cd: 30.07 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-lwk80120k25-il-100000-n5.txt
Download as CSV file: xf-lwk80120k25-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: LWK 80-120/K25                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.250  -0.7469   0.08967   0.08429  -0.0321   1.0000   0.0290
 -13.000  -0.7711   0.08125   0.07578  -0.0377   1.0000   0.0287
 -12.750  -0.7952   0.07422   0.06861  -0.0419   1.0000   0.0284
 -12.500  -0.8247   0.06755   0.06174  -0.0447   1.0000   0.0284
 -12.250  -0.8453   0.06273   0.05673  -0.0456   1.0000   0.0284
 -12.000  -0.8671   0.05824   0.05198  -0.0454   1.0000   0.0285
 -11.750  -0.8844   0.05445   0.04792  -0.0442   1.0000   0.0286
 -11.500  -0.8997   0.05101   0.04417  -0.0423   1.0000   0.0287
 -11.250  -0.9124   0.04795   0.04075  -0.0395   1.0000   0.0291
 -11.000  -0.9155   0.04535   0.03796  -0.0371   1.0000   0.0295
 -10.750  -0.9135   0.04346   0.03599  -0.0348   1.0000   0.0303
 -10.500  -0.9096   0.04167   0.03404  -0.0326   1.0000   0.0310
 -10.250  -0.9028   0.04017   0.03239  -0.0306   1.0000   0.0324
 -10.000  -0.8949   0.03846   0.03043  -0.0285   1.0000   0.0341
  -9.750  -0.8846   0.03640   0.02803  -0.0266   1.0000   0.0358
  -9.500  -0.8709   0.03435   0.02565  -0.0249   1.0000   0.0373
  -9.250  -0.8559   0.03278   0.02407  -0.0237   1.0000   0.0391
  -9.000  -0.8412   0.03167   0.02287  -0.0222   1.0000   0.0413
  -8.750  -0.8256   0.03048   0.02150  -0.0206   1.0000   0.0444
  -8.500  -0.8081   0.02912   0.01992  -0.0192   1.0000   0.0471
  -8.250  -0.7941   0.02797   0.01882  -0.0174   1.0000   0.0497
  -8.000  -0.7822   0.02717   0.01799  -0.0152   1.0000   0.0529
  -7.750  -0.7719   0.02646   0.01713  -0.0124   1.0000   0.0568
  -7.500  -0.7663   0.02566   0.01630  -0.0090   1.0000   0.0598
  -7.250  -0.7437   0.02475   0.01537  -0.0090   0.9922   0.0650
  -7.000  -0.7152   0.02378   0.01430  -0.0099   0.9854   0.0720
  -6.750  -0.6863   0.02288   0.01337  -0.0110   0.9800   0.0798
  -6.500  -0.6599   0.02202   0.01250  -0.0115   0.9735   0.0887
  -6.000  -0.6038   0.02049   0.01092  -0.0130   0.9630   0.1133
  -5.750  -0.5752   0.01972   0.01022  -0.0140   0.9584   0.1313
  -5.500  -0.5486   0.01901   0.00958  -0.0145   0.9536   0.1575
  -5.250  -0.5254   0.01828   0.00905  -0.0143   0.9481   0.1963
  -5.000  -0.5013   0.01739   0.00853  -0.0145   0.9435   0.2642
  -4.750  -0.4848   0.01648   0.00810  -0.0131   0.9374   0.3589
  -4.500  -0.4697   0.01562   0.00793  -0.0110   0.9316   0.4862
  -4.250  -0.4425   0.01562   0.00849  -0.0099   0.9287   0.6081
  -4.000  -0.4169   0.01592   0.00881  -0.0087   0.9245   0.6636
  -3.750  -0.3942   0.01616   0.00896  -0.0074   0.9193   0.6959
  -3.500  -0.3667   0.01644   0.00914  -0.0068   0.9155   0.7210
  -3.250  -0.3382   0.01674   0.00933  -0.0065   0.9125   0.7423
  -3.000  -0.3193   0.01705   0.00956  -0.0044   0.9071   0.7608
  -2.750  -0.2919   0.01747   0.00991  -0.0035   0.9033   0.7774
  -2.500  -0.2629   0.01781   0.01019  -0.0030   0.9001   0.7924
  -2.250  -0.2300   0.01810   0.01041  -0.0033   0.8978   0.8037
  -2.000  -0.2044   0.01830   0.01054  -0.0026   0.8936   0.8125
  -1.750  -0.1848   0.01833   0.01052  -0.0011   0.8885   0.8226
  -1.500  -0.1511   0.01844   0.01058  -0.0020   0.8857   0.8278
  -1.250  -0.1242   0.01841   0.01048  -0.0020   0.8826   0.8351
  -1.000  -0.1018   0.01846   0.01051  -0.0011   0.8775   0.8405
  -0.750  -0.0754   0.01849   0.01051  -0.0009   0.8733   0.8456
  -0.500  -0.0537   0.01841   0.01039   0.0000   0.8692   0.8524
  -0.250  -0.0215   0.01844   0.01041  -0.0009   0.8661   0.8555
   0.000   0.0000   0.01849   0.01047   0.0000   0.8602   0.8602
   0.250   0.0215   0.01844   0.01041   0.0009   0.8555   0.8661
   0.500   0.0536   0.01841   0.01039   0.0001   0.8524   0.8692
   0.750   0.0754   0.01849   0.01051   0.0009   0.8457   0.8733
   1.000   0.1018   0.01846   0.01051   0.0011   0.8405   0.8775
   1.250   0.1243   0.01841   0.01048   0.0020   0.8352   0.8826
   1.500   0.1511   0.01844   0.01058   0.0020   0.8278   0.8858
   1.750   0.1849   0.01833   0.01051   0.0011   0.8226   0.8885
   2.000   0.2045   0.01829   0.01055   0.0026   0.8124   0.8936
   2.250   0.2300   0.01810   0.01041   0.0034   0.8036   0.8979
   2.500   0.2627   0.01783   0.01020   0.0030   0.7926   0.9001
   2.750   0.2919   0.01747   0.00991   0.0035   0.7775   0.9033
   3.000   0.3193   0.01705   0.00956   0.0044   0.7609   0.9071
   3.250   0.3384   0.01674   0.00933   0.0065   0.7427   0.9125
   3.500   0.3668   0.01643   0.00913   0.0069   0.7207   0.9155
   3.750   0.3941   0.01615   0.00896   0.0074   0.6954   0.9193
   4.000   0.4169   0.01591   0.00881   0.0087   0.6635   0.9246
   4.250   0.4425   0.01562   0.00848   0.0098   0.6078   0.9287
   4.500   0.4695   0.01563   0.00790   0.0111   0.4834   0.9316
   4.750   0.4846   0.01649   0.00810   0.0132   0.3581   0.9374
   5.000   0.5014   0.01740   0.00853   0.0145   0.2640   0.9436
   5.250   0.5255   0.01827   0.00905   0.0143   0.1967   0.9481
   5.500   0.5487   0.01901   0.00958   0.0145   0.1574   0.9536
   5.750   0.5754   0.01972   0.01022   0.0139   0.1311   0.9585
   6.000   0.6040   0.02050   0.01092   0.0130   0.1131   0.9631
   6.250   0.6304   0.02122   0.01163   0.0126   0.0995   0.9691
   6.500   0.6601   0.02202   0.01250   0.0114   0.0884   0.9736
   6.750   0.6865   0.02287   0.01336   0.0109   0.0795   0.9800
   7.000   0.7153   0.02379   0.01430   0.0098   0.0719   0.9855
   7.250   0.7438   0.02477   0.01540   0.0090   0.0653   0.9923
   7.500   0.7662   0.02567   0.01631   0.0090   0.0598   1.0000
   7.750   0.7719   0.02645   0.01712   0.0124   0.0568   1.0000
   8.000   0.7823   0.02718   0.01800   0.0152   0.0530   1.0000
   8.250   0.7939   0.02795   0.01879   0.0175   0.0495   1.0000
   8.500   0.8082   0.02914   0.01994   0.0192   0.0471   1.0000
   8.750   0.8258   0.03052   0.02153   0.0206   0.0444   1.0000
   9.000   0.8414   0.03168   0.02288   0.0222   0.0413   1.0000
   9.250   0.8558   0.03276   0.02404   0.0237   0.0389   1.0000
   9.500   0.8712   0.03436   0.02567   0.0249   0.0374   1.0000
   9.750   0.8847   0.03640   0.02804   0.0266   0.0357   1.0000
  10.000   0.8948   0.03827   0.03024   0.0285   0.0337   1.0000
  10.250   0.9029   0.03991   0.03210   0.0306   0.0319   1.0000
  10.500   0.9099   0.04159   0.03394   0.0325   0.0309   1.0000
  10.750   0.9142   0.04332   0.03581   0.0347   0.0300   1.0000
  11.000   0.9156   0.04541   0.03802   0.0371   0.0295   1.0000
  11.250   0.9114   0.04803   0.04086   0.0396   0.0290   1.0000
  11.500   0.8992   0.05112   0.04430   0.0422   0.0287   1.0000
  11.750   0.8861   0.05439   0.04784   0.0441   0.0286   1.0000
  12.000   0.8653   0.05849   0.05225   0.0453   0.0284   1.0000
  12.250   0.8443   0.06294   0.05694   0.0455   0.0283   1.0000
  12.500   0.8217   0.06805   0.06227   0.0444   0.0284   1.0000
  12.750   0.7927   0.07474   0.06914   0.0414   0.0284   1.0000
  13.000   0.7644   0.08271   0.07726   0.0365   0.0286   1.0000
  13.250   0.7381   0.09201   0.08666   0.0301   0.0289   1.0000
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