Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

LWK 80-120/K25 (lwk80120k25-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: LWK 80-120/K25 (lwk80120k25-il)
Reynolds number: 100,000
Max Cl/Cd: 40.74 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-lwk80120k25-il-100000.txt
Download as CSV file: xf-lwk80120k25-il-100000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.6062   0.07345   0.06865  -0.0434   1.0000   0.0826
 -11.000  -0.6154   0.06771   0.06290  -0.0443   1.0000   0.0812
 -10.750  -0.6427   0.06143   0.05656  -0.0456   1.0000   0.0797
 -10.500  -0.8358   0.06692   0.06116  -0.0373   1.0000   0.0709
 -10.250  -0.8304   0.06213   0.05627  -0.0365   1.0000   0.0690
 -10.000  -0.8382   0.05804   0.05201  -0.0343   1.0000   0.0682
  -9.750  -0.8453   0.05414   0.04787  -0.0316   1.0000   0.0674
  -9.500  -0.8513   0.05056   0.04398  -0.0286   1.0000   0.0674
  -9.250  -0.8566   0.04750   0.04049  -0.0250   1.0000   0.0687
  -9.000  -0.8573   0.04473   0.03729  -0.0216   1.0000   0.0695
  -8.750  -0.8560   0.04236   0.03446  -0.0179   1.0000   0.0703
  -8.500  -0.8510   0.03870   0.03054  -0.0151   1.0000   0.0713
  -8.250  -0.8420   0.03630   0.02806  -0.0127   1.0000   0.0735
  -8.000  -0.8343   0.03512   0.02685  -0.0097   1.0000   0.0769
  -7.750  -0.8301   0.03370   0.02515  -0.0059   1.0000   0.0800
  -7.500  -0.8246   0.03232   0.02336  -0.0021   1.0000   0.0829
  -7.250  -0.8101   0.03010   0.02104  -0.0002   1.0000   0.0867
  -7.000  -0.7977   0.02904   0.01991   0.0022   1.0000   0.0925
  -6.750  -0.7840   0.02788   0.01842   0.0047   1.0000   0.0979
  -6.500  -0.7656   0.02636   0.01703   0.0059   1.0000   0.1052
  -6.250  -0.7493   0.02527   0.01579   0.0078   1.0000   0.1134
  -6.000  -0.7321   0.02424   0.01481   0.0095   1.0000   0.1223
  -5.750  -0.7159   0.02323   0.01385   0.0112   1.0000   0.1334
  -5.500  -0.7002   0.02229   0.01296   0.0132   1.0000   0.1459
  -5.250  -0.6860   0.02142   0.01218   0.0153   1.0000   0.1620
  -5.000  -0.6728   0.02056   0.01144   0.0176   1.0000   0.1829
  -4.750  -0.6617   0.01956   0.01068   0.0202   1.0000   0.2145
  -4.500  -0.6554   0.01819   0.00995   0.0235   1.0000   0.2817
  -4.250  -0.6610   0.01622   0.00944   0.0292   1.0000   0.4888
  -4.000  -0.6558   0.01658   0.01069   0.0359   1.0000   0.6886
  -3.750  -0.6445   0.01724   0.01128   0.0402   1.0000   0.7425
  -3.500  -0.6322   0.01787   0.01182   0.0444   1.0000   0.7763
  -3.250  -0.6168   0.01856   0.01243   0.0483   1.0000   0.8022
  -3.000  -0.6021   0.01906   0.01282   0.0520   1.0000   0.8254
  -2.750  -0.5850   0.01953   0.01321   0.0553   1.0000   0.8473
  -2.500  -0.5691   0.01981   0.01339   0.0584   1.0000   0.8680
  -2.250  -0.5368   0.02044   0.01388   0.0589   1.0000   0.8869
  -2.000  -0.4777   0.02161   0.01489   0.0544   0.9992   0.9078
  -1.750  -0.3563   0.02362   0.01664   0.0387   1.0000   0.9295
  -1.500  -0.2986   0.02404   0.01692   0.0327   1.0000   0.9427
  -1.250  -0.2369   0.02424   0.01701   0.0255   0.9988   0.9510
  -1.000  -0.1879   0.02433   0.01701   0.0202   0.9958   0.9587
  -0.750  -0.1388   0.02433   0.01695   0.0149   0.9926   0.9650
  -0.500  -0.0931   0.02438   0.01695   0.0100   0.9892   0.9709
  -0.250  -0.0460   0.02434   0.01689   0.0049   0.9852   0.9760
   0.000  -0.0001   0.02440   0.01693   0.0000   0.9809   0.9808
   0.250   0.0457   0.02434   0.01689  -0.0048   0.9759   0.9850
   0.500   0.0923   0.02438   0.01695  -0.0099   0.9710   0.9891
   0.750   0.1389   0.02433   0.01694  -0.0148   0.9650   0.9926
   1.000   0.1885   0.02432   0.01700  -0.0203   0.9588   0.9959
   1.250   0.2370   0.02423   0.01700  -0.0255   0.9510   0.9988
   1.500   0.3002   0.02401   0.01690  -0.0330   0.9426   1.0000
   1.750   0.3530   0.02367   0.01668  -0.0382   0.9298   1.0000
   2.000   0.4779   0.02161   0.01489  -0.0545   0.9081   0.9993
   2.250   0.5375   0.02041   0.01386  -0.0589   0.8867   1.0000
   2.500   0.5695   0.01979   0.01336  -0.0584   0.8677   1.0000
   2.750   0.5850   0.01953   0.01320  -0.0553   0.8472   1.0000
   3.000   0.6020   0.01905   0.01281  -0.0520   0.8253   1.0000
   3.250   0.6167   0.01856   0.01243  -0.0482   0.8022   1.0000
   3.500   0.6322   0.01786   0.01180  -0.0444   0.7761   1.0000
   3.750   0.6443   0.01724   0.01128  -0.0402   0.7423   1.0000
   4.000   0.6556   0.01656   0.01067  -0.0358   0.6881   1.0000
   4.250   0.6608   0.01622   0.00944  -0.0292   0.4873   1.0000
   4.500   0.6550   0.01821   0.00995  -0.0234   0.2800   1.0000
   4.750   0.6616   0.01956   0.01070  -0.0202   0.2143   1.0000
   5.000   0.6727   0.02055   0.01143  -0.0176   0.1830   1.0000
   5.250   0.6859   0.02140   0.01217  -0.0153   0.1621   1.0000
   5.500   0.7001   0.02229   0.01295  -0.0131   0.1458   1.0000
   5.750   0.7158   0.02324   0.01385  -0.0112   0.1333   1.0000
   6.000   0.7317   0.02421   0.01478  -0.0094   0.1218   1.0000
   6.250   0.7493   0.02528   0.01580  -0.0078   0.1134   1.0000
   6.500   0.7659   0.02640   0.01707  -0.0059   0.1053   1.0000
   6.750   0.7840   0.02791   0.01845  -0.0047   0.0978   1.0000
   7.000   0.7972   0.02900   0.01987  -0.0021   0.0922   1.0000
   7.250   0.8099   0.03006   0.02100   0.0002   0.0868   1.0000
   7.500   0.8243   0.03230   0.02334   0.0021   0.0829   1.0000
   7.750   0.8303   0.03374   0.02519   0.0059   0.0803   1.0000
   8.000   0.8341   0.03510   0.02683   0.0098   0.0768   1.0000
   8.250   0.8419   0.03636   0.02812   0.0127   0.0734   1.0000
   8.500   0.8509   0.03874   0.03058   0.0151   0.0713   1.0000
   8.750   0.8550   0.04223   0.03436   0.0181   0.0701   1.0000
   9.000   0.8564   0.04461   0.03720   0.0218   0.0693   1.0000
   9.250   0.8543   0.04734   0.04039   0.0254   0.0679   1.0000
   9.500   0.8520   0.05063   0.04403   0.0285   0.0676   1.0000
   9.750   0.8449   0.05419   0.04793   0.0317   0.0673   1.0000
  10.000   0.8366   0.05808   0.05207   0.0344   0.0680   1.0000
  10.250   0.8270   0.06222   0.05639   0.0368   0.0688   1.0000
  10.500   0.8359   0.06723   0.06147   0.0372   0.0708   1.0000
  10.750   0.6389   0.06134   0.05647   0.0455   0.0790   1.0000
  11.000   0.6153   0.06758   0.06277   0.0443   0.0813   1.0000
  11.250   0.6005   0.07363   0.06884   0.0429   0.0825   1.0000
<< Back to LWK 80-120/K25 (lwk80120k25-il)

Polar data table (+)

Polar graphs


<< Back to LWK 80-120/K25 (lwk80120k25-il)