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LWK 80-080 (lwk80080-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: LWK 80-080 (lwk80080-il)
Reynolds number: 100,000
Max Cl/Cd: 37.42 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-lwk80080-il-100000.txt
Download as CSV file: xf-lwk80080-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: LWK 80-080                                      
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.6271   0.09993   0.09510  -0.0040   1.0000   0.1050
  -9.250  -0.6337   0.09531   0.09053  -0.0076   1.0000   0.1080
  -9.000  -0.6467   0.08997   0.08527  -0.0133   1.0000   0.1093
  -8.750  -0.6737   0.08521   0.08053  -0.0186   1.0000   0.1103
  -8.500  -0.6549   0.08153   0.07692  -0.0158   1.0000   0.1204
  -8.250  -0.6777   0.07748   0.07282  -0.0186   1.0000   0.1231
  -8.000  -0.6937   0.07363   0.06880  -0.0201   1.0000   0.1241
  -7.750  -0.6820   0.06971   0.06497  -0.0186   1.0000   0.1361
  -6.500  -0.6641   0.04401   0.03732  -0.0146   1.0000   0.0827
  -6.250  -0.6500   0.03783   0.03065  -0.0122   1.0000   0.0650
  -6.000  -0.6337   0.03452   0.02628  -0.0087   1.0000   0.0572
  -5.750  -0.6161   0.03092   0.02235  -0.0069   1.0000   0.0564
  -5.500  -0.5964   0.02823   0.01923  -0.0049   1.0000   0.0567
  -5.250  -0.5754   0.02564   0.01628  -0.0033   1.0000   0.0585
  -5.000  -0.5550   0.02384   0.01449  -0.0022   1.0000   0.0657
  -4.750  -0.5319   0.02179   0.01221  -0.0006   1.0000   0.0726
  -4.500  -0.5112   0.02053   0.01088   0.0009   1.0000   0.0833
  -4.250  -0.4921   0.01906   0.00949   0.0027   1.0000   0.0969
  -4.000  -0.4772   0.01758   0.00821   0.0051   1.0000   0.1152
  -3.750  -0.4647   0.01642   0.00727   0.0079   1.0000   0.1500
  -3.500  -0.4594   0.01455   0.00622   0.0118   1.0000   0.2561
  -3.250  -0.4711   0.01260   0.00666   0.0210   1.0000   0.7248
  -3.000  -0.4634   0.01302   0.00713   0.0274   1.0000   0.8231
  -2.750  -0.4412   0.01351   0.00751   0.0312   1.0000   0.8814
  -2.500  -0.2435   0.01557   0.00865   0.0051   1.0000   0.9504
  -2.250  -0.1449   0.01543   0.00812  -0.0083   1.0000   0.9756
  -2.000  -0.0878   0.01500   0.00747  -0.0149   1.0000   0.9894
  -1.750  -0.0341   0.01448   0.00682  -0.0211   1.0000   0.9996
  -1.500  -0.0173   0.01423   0.00655  -0.0201   1.0000   1.0000
  -1.250  -0.0042   0.01405   0.00638  -0.0184   1.0000   1.0000
  -1.000   0.0060   0.01394   0.00628  -0.0162   1.0000   1.0000
  -0.750   0.0110   0.01391   0.00627  -0.0132   1.0000   1.0000
  -0.500   0.0092   0.01397   0.00635  -0.0091   1.0000   1.0000
  -0.250   0.0047   0.01403   0.00641  -0.0045   1.0000   1.0000
   0.000   0.0000   0.01405   0.00642   0.0000   1.0000   1.0000
   0.250  -0.0046   0.01403   0.00640   0.0045   1.0000   1.0000
   0.500  -0.0092   0.01397   0.00634   0.0091   1.0000   1.0000
   0.750  -0.0110   0.01391   0.00627   0.0132   1.0000   1.0000
   1.000  -0.0060   0.01393   0.00627   0.0162   1.0000   1.0000
   1.250   0.0042   0.01405   0.00639   0.0184   1.0000   1.0000
   1.500   0.0174   0.01423   0.00656   0.0201   1.0000   1.0000
   1.750   0.0349   0.01447   0.00683   0.0209   0.9994   1.0000
   2.000   0.0878   0.01500   0.00748   0.0149   0.9893   1.0000
   2.250   0.1473   0.01543   0.00813   0.0079   0.9749   1.0000
   2.500   0.2651   0.01541   0.00857  -0.0087   0.9451   1.0000
   2.750   0.4416   0.01353   0.00752  -0.0314   0.8830   1.0000
   3.000   0.4633   0.01302   0.00713  -0.0274   0.8231   1.0000
   3.250   0.4707   0.01258   0.00661  -0.0208   0.7201   1.0000
   3.500   0.4598   0.01450   0.00620  -0.0119   0.2622   1.0000
   3.750   0.4647   0.01642   0.00728  -0.0079   0.1494   1.0000
   4.000   0.4771   0.01759   0.00823  -0.0051   0.1149   1.0000
   4.250   0.4922   0.01908   0.00953  -0.0027   0.0964   1.0000
   4.500   0.5107   0.02032   0.01076  -0.0008   0.0804   1.0000
   4.750   0.5322   0.02239   0.01272   0.0005   0.0705   1.0000
   5.000   0.5543   0.02371   0.01435   0.0022   0.0635   1.0000
   5.250   0.5751   0.02623   0.01684   0.0032   0.0574   1.0000
   5.500   0.5962   0.02819   0.01927   0.0052   0.0557   1.0000
   5.750   0.6160   0.03096   0.02242   0.0070   0.0562   1.0000
   6.000   0.6333   0.03444   0.02628   0.0089   0.0569   1.0000
   6.250   0.6497   0.03797   0.03074   0.0123   0.0650   1.0000
   6.500   0.6643   0.04427   0.03755   0.0145   0.0829   1.0000
   8.500   0.7048   0.08219   0.07735   0.0209   0.1110   1.0000
   8.750   0.6887   0.08573   0.08102   0.0195   0.1108   1.0000
   9.000   0.6645   0.08957   0.08488   0.0170   0.1103   1.0000
   9.250   0.6472   0.09488   0.09015   0.0113   0.1100   1.0000
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