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LWK 80-080 (lwk80080-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: LWK 80-080 (lwk80080-il)
Reynolds number: 500,000
Max Cl/Cd: 47.17 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-lwk80080-il-500000-n5.txt
Download as CSV file: xf-lwk80080-il-500000-n5.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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.7608   0.07206   0.07000  -0.0134   1.0000   0.0043
 -10.000  -0.7724   0.06516   0.06303  -0.0187   1.0000   0.0042
  -9.750  -0.7988   0.05861   0.05634  -0.0212   1.0000   0.0040
  -9.500  -0.8341   0.04900   0.04643  -0.0202   1.0000   0.0040
  -9.250  -0.8668   0.03740   0.03419  -0.0171   1.0000   0.0041
  -9.000  -0.8672   0.03280   0.02913  -0.0148   1.0000   0.0041
  -8.750  -0.8681   0.02784   0.02358  -0.0119   1.0000   0.0043
  -8.500  -0.8571   0.02527   0.02068  -0.0101   1.0000   0.0047
  -8.250  -0.8433   0.02283   0.01787  -0.0083   1.0000   0.0048
  -8.000  -0.8231   0.02197   0.01689  -0.0074   1.0000   0.0051
  -7.750  -0.7989   0.02234   0.01732  -0.0072   1.0000   0.0057
  -7.500  -0.7814   0.02042   0.01511  -0.0057   1.0000   0.0059
  -7.250  -0.7624   0.01886   0.01327  -0.0043   1.0000   0.0062
  -7.000  -0.7419   0.01768   0.01190  -0.0030   1.0000   0.0069
  -6.750  -0.7204   0.01689   0.01097  -0.0020   1.0000   0.0074
  -6.250  -0.6741   0.01476   0.00855  -0.0007   0.9855   0.0077
  -6.000  -0.6431   0.01355   0.00721  -0.0019   0.9732   0.0090
  -5.750  -0.6077   0.01289   0.00648  -0.0040   0.9642   0.0098
  -5.500  -0.5713   0.01216   0.00561  -0.0062   0.9557   0.0106
  -5.250  -0.5349   0.01156   0.00490  -0.0084   0.9465   0.0114
  -5.000  -0.4984   0.01107   0.00431  -0.0105   0.9375   0.0128
  -4.750  -0.4643   0.01056   0.00378  -0.0122   0.9280   0.0195
  -4.500  -0.4328   0.01026   0.00342  -0.0132   0.9182   0.0241
  -4.250  -0.4031   0.01000   0.00313  -0.0138   0.9091   0.0307
  -4.000  -0.3754   0.00972   0.00285  -0.0140   0.9008   0.0459
  -3.750  -0.3491   0.00949   0.00262  -0.0138   0.8933   0.0584
  -3.500  -0.3234   0.00919   0.00241  -0.0136   0.8864   0.0848
  -3.250  -0.2995   0.00885   0.00221  -0.0129   0.8796   0.1249
  -3.000  -0.2757   0.00849   0.00199  -0.0123   0.8736   0.1778
  -2.750  -0.2533   0.00807   0.00181  -0.0115   0.8679   0.2498
  -2.500  -0.2339   0.00745   0.00161  -0.0101   0.8619   0.3680
  -2.250  -0.2170   0.00674   0.00141  -0.0081   0.8567   0.5090
  -2.000  -0.1999   0.00625   0.00135  -0.0058   0.8512   0.6251
  -1.750  -0.1772   0.00610   0.00135  -0.0046   0.8465   0.6812
  -1.500  -0.1526   0.00604   0.00133  -0.0038   0.8423   0.7141
  -1.250  -0.1277   0.00601   0.00134  -0.0031   0.8375   0.7381
  -1.000  -0.1029   0.00600   0.00138  -0.0023   0.8332   0.7633
  -0.750  -0.0774   0.00600   0.00140  -0.0016   0.8292   0.7807
  -0.500  -0.0517   0.00600   0.00142  -0.0011   0.8245   0.7927
  -0.250  -0.0260   0.00601   0.00144  -0.0005   0.8196   0.8047
   0.000   0.0000   0.00601   0.00145   0.0000   0.8134   0.8136
   0.250   0.0260   0.00601   0.00143   0.0005   0.8045   0.8195
   0.500   0.0517   0.00600   0.00142   0.0011   0.7928   0.8245
   0.750   0.0774   0.00600   0.00140   0.0016   0.7804   0.8292
   1.000   0.1028   0.00600   0.00137   0.0023   0.7623   0.8332
   1.250   0.1278   0.00601   0.00135   0.0031   0.7390   0.8375
   1.500   0.1526   0.00604   0.00134   0.0038   0.7143   0.8422
   1.750   0.1770   0.00611   0.00134   0.0047   0.6793   0.8465
   2.000   0.1999   0.00625   0.00135   0.0058   0.6254   0.8511
   2.250   0.2183   0.00667   0.00140   0.0078   0.5243   0.8566
   2.500   0.2324   0.00756   0.00162   0.0103   0.3455   0.8622
   2.750   0.2527   0.00811   0.00181   0.0115   0.2406   0.8680
   3.000   0.2753   0.00852   0.00202   0.0124   0.1721   0.8736
   3.250   0.2995   0.00885   0.00220   0.0130   0.1244   0.8795
   3.500   0.3232   0.00921   0.00241   0.0136   0.0829   0.8862
   3.750   0.3489   0.00950   0.00263   0.0138   0.0566   0.8932
   4.000   0.3750   0.00976   0.00284   0.0140   0.0387   0.9009
   4.250   0.4031   0.01000   0.00313   0.0138   0.0296   0.9095
   4.500   0.4327   0.01029   0.00344   0.0132   0.0224   0.9185
   4.750   0.4642   0.01059   0.00378   0.0122   0.0165   0.9281
   5.000   0.4984   0.01107   0.00432   0.0106   0.0122   0.9373
   5.250   0.5345   0.01158   0.00492   0.0085   0.0111   0.9462
   5.500   0.5709   0.01220   0.00565   0.0063   0.0099   0.9555
   5.750   0.6076   0.01288   0.00646   0.0040   0.0096   0.9641
   6.000   0.6426   0.01367   0.00733   0.0020   0.0084   0.9734
   6.250   0.6732   0.01508   0.00891   0.0009   0.0077   0.9861
   6.750   0.7206   0.01688   0.01096   0.0020   0.0072   1.0000
   7.000   0.7411   0.01796   0.01221   0.0032   0.0069   1.0000
   7.250   0.7614   0.01917   0.01361   0.0044   0.0064   1.0000
   7.500   0.7802   0.02081   0.01555   0.0059   0.0061   1.0000
   7.750   0.7990   0.02234   0.01732   0.0072   0.0059   1.0000
   8.000   0.8170   0.02388   0.01910   0.0085   0.0056   1.0000
   8.250   0.8407   0.02363   0.01880   0.0087   0.0050   1.0000
   8.500   0.8579   0.02509   0.02046   0.0100   0.0047   1.0000
   8.750   0.8718   0.02718   0.02283   0.0115   0.0045   1.0000
   9.000   0.8763   0.03108   0.02722   0.0139   0.0044   1.0000
   9.250   0.8660   0.03737   0.03415   0.0171   0.0042   1.0000
   9.500   0.8397   0.04764   0.04503   0.0199   0.0041   1.0000
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