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LWK 80-100 (lwk80100-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: LWK 80-100 (lwk80100-il)
Reynolds number: 200,000
Max Cl/Cd: 44 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-lwk80100-il-200000.txt
Download as CSV file: xf-lwk80100-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: LWK 80-100                                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.6531   0.08752   0.08408  -0.0210   1.0000   0.0579
 -10.000  -0.6732   0.07911   0.07568  -0.0286   1.0000   0.0576
  -9.750  -0.6939   0.07334   0.06985  -0.0320   1.0000   0.0580
  -9.500  -0.7153   0.06881   0.06525  -0.0329   1.0000   0.0581
  -9.250  -0.7075   0.04239   0.03846  -0.0340   1.0000   0.0399
  -9.000  -0.7211   0.03720   0.03315  -0.0317   1.0000   0.0382
  -8.750  -0.8180   0.04242   0.03702  -0.0215   1.0000   0.0315
  -8.500  -0.8068   0.04054   0.03482  -0.0192   1.0000   0.0308
  -8.250  -0.7973   0.03744   0.03141  -0.0170   1.0000   0.0304
  -8.000  -0.7908   0.03400   0.02756  -0.0142   1.0000   0.0307
  -7.750  -0.7827   0.02967   0.02281  -0.0118   1.0000   0.0314
  -7.500  -0.7678   0.02792   0.02101  -0.0104   1.0000   0.0338
  -7.250  -0.7517   0.02628   0.01919  -0.0085   1.0000   0.0352
  -7.000  -0.7363   0.02456   0.01726  -0.0063   1.0000   0.0368
  -6.750  -0.7243   0.02317   0.01566  -0.0034   1.0000   0.0386
  -6.500  -0.7146   0.02223   0.01451  -0.0001   1.0000   0.0403
  -6.250  -0.7030   0.02052   0.01267   0.0026   1.0000   0.0432
  -6.000  -0.6921   0.01994   0.01212   0.0052   1.0000   0.0474
  -5.750  -0.6783   0.01937   0.01141   0.0076   1.0000   0.0521
  -5.500  -0.6529   0.01803   0.01010   0.0075   0.9978   0.0585
  -5.250  -0.6209   0.01717   0.00916   0.0062   0.9938   0.0677
  -5.000  -0.5881   0.01643   0.00839   0.0047   0.9902   0.0788
  -4.750  -0.5588   0.01558   0.00757   0.0039   0.9859   0.0930
  -4.500  -0.5294   0.01466   0.00681   0.0028   0.9820   0.1161
  -4.250  -0.5036   0.01375   0.00617   0.0025   0.9772   0.1609
  -4.000  -0.4833   0.01224   0.00556   0.0027   0.9720   0.3254
  -3.750  -0.4738   0.01079   0.00541   0.0057   0.9662   0.5863
  -3.500  -0.4501   0.01083   0.00580   0.0073   0.9615   0.7035
  -3.250  -0.4182   0.01109   0.00605   0.0070   0.9583   0.7498
  -3.000  -0.3831   0.01135   0.00626   0.0060   0.9561   0.7759
  -2.750  -0.3626   0.01160   0.00644   0.0079   0.9503   0.7954
  -2.500  -0.3325   0.01185   0.00663   0.0079   0.9468   0.8138
  -2.250  -0.2981   0.01204   0.00678   0.0070   0.9444   0.8283
  -2.000  -0.2620   0.01228   0.00696   0.0059   0.9426   0.8431
  -1.750  -0.2381   0.01254   0.00722   0.0074   0.9381   0.8585
  -1.500  -0.2097   0.01279   0.00746   0.0081   0.9345   0.8733
  -1.250  -0.1771   0.01295   0.00760   0.0076   0.9317   0.8857
  -1.000  -0.1357   0.01310   0.00771   0.0053   0.9300   0.8934
  -0.750  -0.0983   0.01311   0.00769   0.0034   0.9278   0.9003
  -0.500  -0.0685   0.01321   0.00778   0.0029   0.9231   0.9059
  -0.250  -0.0442   0.01318   0.00772   0.0034   0.9178   0.9133
   0.000   0.0000   0.01318   0.00772   0.0000   0.9155   0.9155
   0.250   0.0442   0.01318   0.00772  -0.0034   0.9133   0.9178
   0.500   0.0686   0.01321   0.00778  -0.0029   0.9059   0.9230
   0.750   0.0984   0.01312   0.00769  -0.0034   0.9004   0.9278
   1.000   0.1357   0.01309   0.00771  -0.0053   0.8933   0.9300
   1.250   0.1776   0.01293   0.00757  -0.0076   0.8853   0.9315
   1.500   0.2100   0.01278   0.00746  -0.0081   0.8732   0.9345
   1.750   0.2382   0.01255   0.00723  -0.0074   0.8587   0.9382
   2.000   0.2624   0.01227   0.00695  -0.0059   0.8429   0.9426
   2.250   0.2982   0.01204   0.00676  -0.0070   0.8280   0.9444
   2.500   0.3328   0.01184   0.00661  -0.0079   0.8134   0.9468
   2.750   0.3628   0.01161   0.00644  -0.0079   0.7954   0.9503
   3.000   0.3832   0.01136   0.00627  -0.0060   0.7764   0.9561
   3.250   0.4185   0.01109   0.00606  -0.0070   0.7501   0.9583
   3.500   0.4504   0.01084   0.00582  -0.0073   0.7059   0.9615
   3.750   0.4743   0.01078   0.00543  -0.0058   0.5908   0.9661
   4.000   0.4837   0.01221   0.00555  -0.0027   0.3297   0.9720
   4.250   0.5040   0.01373   0.00616  -0.0025   0.1641   0.9772
   4.500   0.5298   0.01462   0.00677  -0.0029   0.1190   0.9820
   4.750   0.5601   0.01543   0.00747  -0.0040   0.0949   0.9857
   5.000   0.5886   0.01638   0.00834  -0.0048   0.0797   0.9902
   5.250   0.6212   0.01714   0.00914  -0.0063   0.0676   0.9939
   5.500   0.6533   0.01796   0.01002  -0.0076   0.0579   0.9978
   5.750   0.6783   0.01923   0.01130  -0.0075   0.0511   1.0000
   6.000   0.6914   0.01967   0.01183  -0.0051   0.0459   1.0000
   6.250   0.7029   0.02131   0.01344  -0.0027   0.0411   1.0000
   6.500   0.7138   0.02200   0.01431   0.0004   0.0392   1.0000
   6.750   0.7237   0.02307   0.01558   0.0036   0.0374   1.0000
   7.000   0.7360   0.02444   0.01712   0.0064   0.0358   1.0000
   7.250   0.7516   0.02605   0.01892   0.0085   0.0345   1.0000
   7.500   0.7676   0.02739   0.02035   0.0102   0.0326   1.0000
   7.750   0.7807   0.03051   0.02368   0.0120   0.0310   1.0000
   8.000   0.7889   0.03427   0.02788   0.0146   0.0304   1.0000
   8.250   0.7969   0.03749   0.03149   0.0172   0.0304   1.0000
   8.500   0.8019   0.04168   0.03603   0.0197   0.0307   1.0000
   8.750   0.8147   0.04323   0.03784   0.0218   0.0312   1.0000
   9.000   0.7434   0.06174   0.05796   0.0300   0.0597   1.0000
   9.250   0.7316   0.06545   0.06181   0.0314   0.0588   1.0000
   9.500   0.7148   0.06891   0.06535   0.0329   0.0578   1.0000
   9.750   0.6938   0.07343   0.06994   0.0320   0.0578   1.0000
  10.000   0.6724   0.07938   0.07594   0.0282   0.0578   1.0000
  10.250   0.6543   0.08731   0.08387   0.0214   0.0573   1.0000
  10.500   0.6501   0.09268   0.08921   0.0181   0.0563   1.0000
  10.750   0.6481   0.09752   0.09403   0.0158   0.0556   1.0000
  11.000   0.6476   0.10215   0.09864   0.0140   0.0550   1.0000
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