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LWK 80-120/K25 (lwk80120k25-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: LWK 80-120/K25 (lwk80120k25-il)
Reynolds number: 200,000
Max Cl/Cd: 41.43 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-lwk80120k25-il-200000.txt
Download as CSV file: xf-lwk80120k25-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.7177   0.08976   0.08602  -0.0329   1.0000   0.0367
 -12.500  -0.7492   0.08010   0.07627  -0.0391   1.0000   0.0364
 -12.250  -0.7708   0.07365   0.06974  -0.0424   1.0000   0.0358
 -12.000  -0.7970   0.06759   0.06355  -0.0447   1.0000   0.0353
 -11.750  -0.8215   0.06250   0.05830  -0.0455   1.0000   0.0349
 -11.500  -0.8453   0.05798   0.05359  -0.0449   1.0000   0.0345
 -11.250  -0.8684   0.05391   0.04930  -0.0430   1.0000   0.0342
 -11.000  -0.8885   0.05028   0.04544  -0.0400   1.0000   0.0338
 -10.750  -0.9076   0.04695   0.04183  -0.0357   1.0000   0.0339
 -10.500  -0.9179   0.04356   0.03813  -0.0321   1.0000   0.0337
 -10.250  -0.9220   0.04037   0.03458  -0.0288   1.0000   0.0341
 -10.000  -0.9202   0.03763   0.03150  -0.0259   1.0000   0.0347
  -9.750  -0.9142   0.03546   0.02899  -0.0232   1.0000   0.0357
  -9.500  -0.9056   0.03379   0.02698  -0.0206   1.0000   0.0367
  -9.250  -0.8953   0.03059   0.02352  -0.0187   1.0000   0.0385
  -9.000  -0.8802   0.02903   0.02189  -0.0171   1.0000   0.0398
  -8.750  -0.8681   0.02786   0.02061  -0.0148   1.0000   0.0414
  -8.500  -0.8647   0.02703   0.01969  -0.0109   1.0000   0.0430
  -8.250  -0.8651   0.02639   0.01891  -0.0063   1.0000   0.0445
  -8.000  -0.8595   0.02584   0.01818  -0.0027   0.9998   0.0462
  -7.750  -0.8281   0.02383   0.01613  -0.0043   0.9967   0.0504
  -7.500  -0.7959   0.02287   0.01507  -0.0058   0.9925   0.0553
  -7.250  -0.7638   0.02153   0.01364  -0.0073   0.9894   0.0608
  -7.000  -0.7329   0.02070   0.01280  -0.0085   0.9854   0.0672
  -6.750  -0.7019   0.01961   0.01169  -0.0098   0.9820   0.0745
  -6.500  -0.6691   0.01897   0.01098  -0.0113   0.9788   0.0830
  -6.250  -0.6418   0.01803   0.01011  -0.0120   0.9741   0.0927
  -6.000  -0.6105   0.01718   0.00929  -0.0134   0.9708   0.1048
  -5.750  -0.5812   0.01644   0.00861  -0.0144   0.9673   0.1203
  -5.500  -0.5563   0.01578   0.00800  -0.0145   0.9626   0.1415
  -5.250  -0.5289   0.01484   0.00735  -0.0154   0.9591   0.1821
  -5.000  -0.5057   0.01359   0.00670  -0.0157   0.9555   0.2848
  -4.750  -0.4997   0.01255   0.00634  -0.0124   0.9480   0.4169
  -4.500  -0.4852   0.01171   0.00641  -0.0098   0.9438   0.5918
  -4.250  -0.4582   0.01188   0.00676  -0.0091   0.9408   0.6715
  -4.000  -0.4383   0.01221   0.00709  -0.0071   0.9353   0.7055
  -3.750  -0.4111   0.01252   0.00732  -0.0066   0.9316   0.7311
  -3.500  -0.3790   0.01291   0.00766  -0.0068   0.9293   0.7492
  -3.250  -0.3455   0.01330   0.00800  -0.0074   0.9273   0.7648
  -3.000  -0.3292   0.01364   0.00829  -0.0048   0.9215   0.7776
  -2.750  -0.3022   0.01399   0.00860  -0.0042   0.9180   0.7899
  -2.500  -0.2690   0.01437   0.00896  -0.0045   0.9156   0.7997
  -2.250  -0.2366   0.01474   0.00930  -0.0046   0.9134   0.8115
  -2.000  -0.2159   0.01509   0.00963  -0.0028   0.9092   0.8237
  -1.750  -0.1901   0.01547   0.00999  -0.0017   0.9053   0.8339
  -1.500  -0.1589   0.01571   0.01022  -0.0018   0.9023   0.8421
  -1.250  -0.1325   0.01581   0.01028  -0.0014   0.8991   0.8514
  -1.000  -0.0946   0.01595   0.01040  -0.0029   0.8973   0.8561
  -0.750  -0.0801   0.01610   0.01055  -0.0005   0.8910   0.8634
  -0.500  -0.0557   0.01608   0.01051   0.0001   0.8868   0.8694
  -0.250  -0.0194   0.01612   0.01054  -0.0014   0.8842   0.8728
   0.000   0.0000   0.01616   0.01058   0.0000   0.8788   0.8787
   0.250   0.0193   0.01611   0.01054   0.0014   0.8727   0.8841
   0.500   0.0556   0.01608   0.01051  -0.0001   0.8694   0.8868
   0.750   0.0801   0.01610   0.01055   0.0005   0.8634   0.8911
   1.000   0.0949   0.01595   0.01040   0.0029   0.8561   0.8974
   1.250   0.1322   0.01581   0.01028   0.0015   0.8512   0.8992
   1.500   0.1589   0.01571   0.01021   0.0018   0.8421   0.9023
   1.750   0.1903   0.01548   0.01000   0.0016   0.8343   0.9052
   2.000   0.2160   0.01509   0.00962   0.0028   0.8237   0.9092
   2.250   0.2367   0.01474   0.00929   0.0047   0.8115   0.9134
   2.500   0.2691   0.01437   0.00896   0.0045   0.7997   0.9156
   2.750   0.3015   0.01398   0.00858   0.0043   0.7889   0.9181
   3.000   0.3292   0.01364   0.00829   0.0048   0.7777   0.9215
   3.250   0.3456   0.01330   0.00800   0.0074   0.7648   0.9273
   3.500   0.3791   0.01291   0.00767   0.0068   0.7493   0.9293
   3.750   0.4112   0.01251   0.00731   0.0066   0.7309   0.9317
   4.000   0.4382   0.01220   0.00708   0.0071   0.7051   0.9353
   4.250   0.4581   0.01187   0.00675   0.0091   0.6710   0.9408
   4.500   0.4852   0.01171   0.00641   0.0098   0.5914   0.9438
   4.750   0.4999   0.01254   0.00634   0.0123   0.4184   0.9480
   5.000   0.5055   0.01359   0.00670   0.0158   0.2845   0.9556
   5.250   0.5290   0.01483   0.00735   0.0153   0.1827   0.9591
   5.500   0.5562   0.01579   0.00802   0.0145   0.1412   0.9627
   5.750   0.5812   0.01644   0.00861   0.0144   0.1203   0.9674
   6.000   0.6106   0.01717   0.00928   0.0134   0.1041   0.9709
   6.250   0.6418   0.01803   0.01011   0.0120   0.0927   0.9741
   6.500   0.6692   0.01898   0.01099   0.0114   0.0829   0.9788
   6.750   0.7021   0.01961   0.01169   0.0098   0.0742   0.9821
   7.000   0.7332   0.02068   0.01278   0.0085   0.0668   0.9855
   7.250   0.7641   0.02153   0.01366   0.0072   0.0611   0.9894
   7.500   0.7962   0.02295   0.01515   0.0058   0.0555   0.9925
   7.750   0.8285   0.02387   0.01618   0.0043   0.0506   0.9967
   8.000   0.8596   0.02566   0.01801   0.0027   0.0460   1.0000
   8.250   0.8637   0.02623   0.01875   0.0065   0.0442   1.0000
   8.500   0.8639   0.02697   0.01962   0.0110   0.0428   1.0000
   8.750   0.8676   0.02779   0.02054   0.0149   0.0412   1.0000
   9.000   0.8801   0.02896   0.02181   0.0171   0.0397   1.0000
   9.250   0.8954   0.03079   0.02367   0.0185   0.0379   1.0000
   9.500   0.9061   0.03404   0.02723   0.0204   0.0369   1.0000
   9.750   0.9142   0.03545   0.02899   0.0232   0.0357   1.0000
  10.000   0.9200   0.03760   0.03148   0.0259   0.0344   1.0000
  10.250   0.9219   0.04027   0.03449   0.0289   0.0336   1.0000
  10.500   0.9179   0.04355   0.03812   0.0321   0.0336   1.0000
  10.750   0.9068   0.04699   0.04188   0.0358   0.0336   1.0000
  11.000   0.8888   0.05029   0.04545   0.0399   0.0338   1.0000
  11.250   0.8673   0.05406   0.04946   0.0430   0.0341   1.0000
  11.500   0.8442   0.05812   0.05375   0.0448   0.0343   1.0000
  11.750   0.8220   0.06252   0.05833   0.0453   0.0349   1.0000
  12.000   0.7951   0.06795   0.06392   0.0444   0.0353   1.0000
  12.250   0.7679   0.07417   0.07028   0.0418   0.0356   1.0000
  12.500   0.7385   0.08207   0.07830   0.0370   0.0360   1.0000
  12.750   0.7150   0.09067   0.08694   0.0319   0.0367   1.0000
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