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LWK 79-100 (lwk79100-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: LWK 79-100 (lwk79100-il)
Reynolds number: 200,000
Max Cl/Cd: 44.38 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-lwk79100-il-200000-n5.txt
Download as CSV file: xf-lwk79100-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: LWK 79-100                                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.750  -0.9021   0.09534   0.09153   0.0083   1.0000   0.0164
 -13.500  -0.9436   0.08143   0.07741  -0.0013   1.0000   0.0160
 -13.250  -0.9723   0.07167   0.06745  -0.0083   1.0000   0.0158
 -13.000  -0.9949   0.06401   0.05958  -0.0136   1.0000   0.0158
 -12.750  -1.0134   0.05778   0.05313  -0.0176   1.0000   0.0159
 -12.500  -1.0285   0.05257   0.04771  -0.0204   1.0000   0.0160
 -12.250  -1.0404   0.04822   0.04313  -0.0222   1.0000   0.0161
 -12.000  -1.0505   0.04451   0.03919  -0.0231   1.0000   0.0164
 -11.750  -1.0581   0.04148   0.03592  -0.0228   1.0000   0.0166
 -11.500  -1.0629   0.03896   0.03317  -0.0213   1.0000   0.0169
 -11.250  -1.0630   0.03675   0.03070  -0.0195   1.0000   0.0172
 -11.000  -1.0570   0.03464   0.02832  -0.0181   1.0000   0.0177
 -10.750  -1.0482   0.03269   0.02626  -0.0169   1.0000   0.0182
 -10.500  -1.0349   0.03134   0.02482  -0.0160   1.0000   0.0189
 -10.250  -1.0195   0.03015   0.02352  -0.0151   1.0000   0.0198
 -10.000  -1.0029   0.02892   0.02212  -0.0142   1.0000   0.0209
  -9.750  -0.9853   0.02764   0.02063  -0.0133   1.0000   0.0222
  -9.500  -0.9673   0.02628   0.01908  -0.0123   1.0000   0.0233
  -9.250  -0.9498   0.02493   0.01769  -0.0115   1.0000   0.0244
  -9.000  -0.9298   0.02394   0.01661  -0.0107   1.0000   0.0257
  -8.750  -0.9088   0.02303   0.01560  -0.0100   1.0000   0.0275
  -8.500  -0.8870   0.02220   0.01460  -0.0093   1.0000   0.0294
  -8.250  -0.8669   0.02107   0.01343  -0.0085   1.0000   0.0313
  -8.000  -0.8450   0.02026   0.01257  -0.0079   1.0000   0.0335
  -7.750  -0.8222   0.01955   0.01178  -0.0073   1.0000   0.0361
  -7.500  -0.7990   0.01887   0.01099  -0.0066   1.0000   0.0384
  -7.250  -0.7775   0.01792   0.01002  -0.0059   1.0000   0.0413
  -7.000  -0.7540   0.01730   0.00935  -0.0053   1.0000   0.0450
  -6.750  -0.7301   0.01671   0.00867  -0.0047   1.0000   0.0487
  -6.500  -0.7069   0.01598   0.00796  -0.0041   1.0000   0.0534
  -6.250  -0.6824   0.01547   0.00736  -0.0036   1.0000   0.0595
  -6.000  -0.6586   0.01484   0.00679  -0.0031   1.0000   0.0682
  -5.750  -0.6343   0.01430   0.00626  -0.0026   1.0000   0.0792
  -5.500  -0.6098   0.01378   0.00580  -0.0021   1.0000   0.0950
  -5.250  -0.5853   0.01326   0.00536  -0.0016   1.0000   0.1157
  -5.000  -0.5607   0.01279   0.00498  -0.0012   1.0000   0.1394
  -4.750  -0.5361   0.01233   0.00462  -0.0007   1.0000   0.1671
  -4.500  -0.5116   0.01186   0.00430  -0.0003   1.0000   0.1988
  -4.250  -0.4873   0.01140   0.00399   0.0002   1.0000   0.2354
  -4.000  -0.4632   0.01092   0.00372   0.0007   1.0000   0.2801
  -3.750  -0.4389   0.01047   0.00352   0.0012   0.9991   0.3330
  -3.500  -0.4005   0.01010   0.00334  -0.0012   0.9514   0.3892
  -3.250  -0.3579   0.00987   0.00321  -0.0043   0.8905   0.4381
  -3.000  -0.3248   0.00979   0.00310  -0.0050   0.8428   0.4746
  -2.750  -0.2970   0.00979   0.00303  -0.0046   0.8115   0.5031
  -2.500  -0.2704   0.00980   0.00298  -0.0041   0.7890   0.5266
  -2.250  -0.2438   0.00983   0.00293  -0.0035   0.7708   0.5469
  -2.000  -0.2170   0.00985   0.00289  -0.0031   0.7556   0.5651
  -1.750  -0.1902   0.00988   0.00285  -0.0026   0.7425   0.5816
  -1.500  -0.1632   0.00990   0.00282  -0.0022   0.7307   0.5963
  -1.250  -0.1360   0.00991   0.00280  -0.0018   0.7196   0.6097
  -1.000  -0.1088   0.00991   0.00279  -0.0014   0.7094   0.6224
  -0.750  -0.0818   0.00993   0.00278  -0.0010   0.7001   0.6348
  -0.500  -0.0545   0.00992   0.00278  -0.0007   0.6901   0.6477
  -0.250  -0.0273   0.00993   0.00278  -0.0003   0.6809   0.6604
   0.000   0.0000   0.00995   0.00278   0.0000   0.6715   0.6715
   0.250   0.0273   0.00993   0.00278   0.0003   0.6604   0.6809
   0.500   0.0545   0.00992   0.00278   0.0007   0.6477   0.6901
   0.750   0.0818   0.00993   0.00278   0.0010   0.6348   0.7001
   1.000   0.1089   0.00991   0.00279   0.0014   0.6225   0.7094
   1.250   0.1360   0.00991   0.00280   0.0018   0.6097   0.7195
   1.500   0.1632   0.00990   0.00282   0.0022   0.5963   0.7307
   1.750   0.1902   0.00988   0.00285   0.0026   0.5816   0.7425
   2.000   0.2170   0.00985   0.00289   0.0031   0.5652   0.7556
   2.250   0.2438   0.00983   0.00293   0.0035   0.5469   0.7707
   2.500   0.2704   0.00980   0.00298   0.0041   0.5265   0.7889
   2.750   0.2970   0.00979   0.00303   0.0046   0.5030   0.8115
   3.000   0.3248   0.00979   0.00310   0.0050   0.4746   0.8429
   3.250   0.3579   0.00986   0.00321   0.0043   0.4384   0.8905
   3.500   0.4006   0.01010   0.00334   0.0012   0.3896   0.9515
   3.750   0.4389   0.01047   0.00352  -0.0012   0.3331   0.9993
   4.000   0.4632   0.01092   0.00372  -0.0007   0.2800   1.0000
   4.250   0.4872   0.01140   0.00399  -0.0002   0.2353   1.0000
   4.500   0.5115   0.01186   0.00430   0.0003   0.1988   1.0000
   4.750   0.5361   0.01232   0.00462   0.0007   0.1673   1.0000
   5.000   0.5606   0.01280   0.00498   0.0012   0.1393   1.0000
   5.250   0.5853   0.01326   0.00536   0.0016   0.1156   1.0000
   5.500   0.6098   0.01378   0.00580   0.0021   0.0950   1.0000
   5.750   0.6343   0.01430   0.00626   0.0026   0.0792   1.0000
   6.000   0.6586   0.01484   0.00679   0.0031   0.0682   1.0000
   6.250   0.6825   0.01547   0.00736   0.0036   0.0595   1.0000
   6.500   0.7070   0.01598   0.00796   0.0041   0.0534   1.0000
   6.750   0.7301   0.01672   0.00868   0.0047   0.0486   1.0000
   7.000   0.7540   0.01730   0.00935   0.0053   0.0450   1.0000
   7.250   0.7776   0.01793   0.01003   0.0059   0.0414   1.0000
   7.500   0.7991   0.01888   0.01099   0.0066   0.0383   1.0000
   7.750   0.8223   0.01955   0.01178   0.0072   0.0361   1.0000
   8.000   0.8451   0.02027   0.01258   0.0078   0.0335   1.0000
   8.250   0.8671   0.02107   0.01343   0.0085   0.0313   1.0000
   8.500   0.8871   0.02220   0.01460   0.0093   0.0294   1.0000
   8.750   0.9090   0.02303   0.01560   0.0100   0.0275   1.0000
   9.000   0.9300   0.02394   0.01662   0.0107   0.0257   1.0000
   9.250   0.9499   0.02494   0.01770   0.0114   0.0244   1.0000
   9.500   0.9676   0.02629   0.01909   0.0123   0.0233   1.0000
   9.750   0.9856   0.02764   0.02064   0.0132   0.0222   1.0000
  10.000   1.0032   0.02895   0.02215   0.0141   0.0210   1.0000
  10.250   1.0200   0.03012   0.02349   0.0150   0.0197   1.0000
  10.500   1.0354   0.03134   0.02482   0.0159   0.0189   1.0000
  10.750   1.0487   0.03270   0.02627   0.0169   0.0182   1.0000
  11.000   1.0574   0.03466   0.02833   0.0180   0.0177   1.0000
  11.250   1.0637   0.03674   0.03069   0.0194   0.0172   1.0000
  11.500   1.0638   0.03898   0.03318   0.0212   0.0169   1.0000
  11.750   1.0586   0.04151   0.03596   0.0227   0.0165   1.0000
  12.000   1.0514   0.04451   0.03919   0.0230   0.0163   1.0000
  12.250   1.0413   0.04822   0.04314   0.0221   0.0160   1.0000
  12.500   1.0296   0.05256   0.04770   0.0202   0.0160   1.0000
  12.750   1.0146   0.05777   0.05312   0.0174   0.0159   1.0000
  13.000   0.9961   0.06402   0.05959   0.0134   0.0159   1.0000
  13.250   0.9734   0.07170   0.06748   0.0081   0.0159   1.0000
  13.500   0.9445   0.08152   0.07751   0.0011   0.0160   1.0000
  13.750   0.9047   0.09505   0.09123  -0.0083   0.0165   1.0000
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