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EPPLER 541 AIRFOIL (e541-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 541 AIRFOIL (e541-il)
Reynolds number: 200,000
Max Cl/Cd: 50.75 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e541-il-200000-n5.txt
Download as CSV file: xf-e541-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 541 AIRFOIL                              
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.4079   0.08546   0.08197  -0.0847   0.9594   0.0086
 -12.000  -0.4461   0.06927   0.06554  -0.0966   0.9504   0.0080
 -11.750  -0.4886   0.05767   0.05344  -0.1022   0.9401   0.0076
 -11.500  -0.5036   0.05162   0.04694  -0.1041   0.9294   0.0073
 -11.250  -0.5083   0.04773   0.04270  -0.1048   0.9185   0.0072
 -11.000  -0.5167   0.04394   0.03854  -0.1040   0.9079   0.0073
 -10.500  -0.5186   0.03873   0.03266  -0.1008   0.8900   0.0072
 -10.250  -0.5133   0.03680   0.03044  -0.0991   0.8833   0.0071
 -10.000  -0.5118   0.03414   0.02742  -0.0964   0.8764   0.0072
  -9.750  -0.5012   0.03191   0.02486  -0.0949   0.8715   0.0073
  -9.500  -0.4861   0.03027   0.02293  -0.0936   0.8666   0.0073
  -9.250  -0.4677   0.02851   0.02094  -0.0928   0.8621   0.0075
  -9.000  -0.4447   0.02710   0.01929  -0.0925   0.8584   0.0076
  -8.750  -0.4221   0.02587   0.01791  -0.0921   0.8549   0.0078
  -8.500  -0.4005   0.02486   0.01679  -0.0915   0.8508   0.0083
  -8.250  -0.3781   0.02393   0.01574  -0.0909   0.8473   0.0086
  -8.000  -0.3565   0.02309   0.01478  -0.0903   0.8442   0.0090
  -7.750  -0.3366   0.02226   0.01384  -0.0893   0.8412   0.0098
  -7.500  -0.3189   0.02159   0.01305  -0.0881   0.8375   0.0102
  -7.250  -0.3022   0.02088   0.01228  -0.0867   0.8339   0.0116
  -7.000  -0.2833   0.02040   0.01178  -0.0858   0.8307   0.0143
  -6.750  -0.2650   0.01986   0.01112  -0.0846   0.8280   0.0157
  -6.500  -0.2513   0.01916   0.01039  -0.0826   0.8244   0.0189
  -6.250  -0.2357   0.01861   0.00983  -0.0809   0.8212   0.0260
  -6.000  -0.2207   0.01803   0.00930  -0.0791   0.8183   0.0388
  -5.750  -0.2072   0.01742   0.00880  -0.0772   0.8157   0.0696
  -5.500  -0.1974   0.01671   0.00836  -0.0748   0.8130   0.1231
  -5.250  -0.1949   0.01594   0.00797  -0.0711   0.8090   0.1963
  -5.000  -0.2007   0.01510   0.00754  -0.0659   0.8051   0.2846
  -4.750  -0.2154   0.01428   0.00716  -0.0588   0.8018   0.3817
  -4.500  -0.1522   0.01662   0.01090  -0.0605   0.8018   0.6781
  -4.250  -0.1574   0.01638   0.01058  -0.0550   0.7989   0.7002
  -4.000  -0.1545   0.01635   0.01048  -0.0508   0.7951   0.7185
  -3.750  -0.1399   0.01666   0.01068  -0.0483   0.7921   0.7341
  -3.500  -0.1209   0.01729   0.01121  -0.0462   0.7898   0.7507
  -3.250  -0.0508   0.01953   0.01334  -0.0512   0.7896   0.7586
  -3.000  -0.0305   0.01969   0.01340  -0.0498   0.7877   0.7667
  -2.750   0.0009   0.01975   0.01334  -0.0506   0.7863   0.7684
  -2.250   0.0239   0.01945   0.01293  -0.0456   0.7802   0.7793
  -2.000   0.0511   0.01948   0.01290  -0.0457   0.7781   0.7805
  -1.750   0.0781   0.01948   0.01283  -0.0458   0.7761   0.7818
  -1.500   0.1040   0.01942   0.01270  -0.0457   0.7742   0.7835
  -1.250   0.1285   0.01932   0.01254  -0.0455   0.7725   0.7858
  -1.000   0.1297   0.01891   0.01209  -0.0416   0.7694   0.7930
  -0.750   0.1522   0.01895   0.01212  -0.0409   0.7665   0.7940
  -0.500   0.1764   0.01895   0.01210  -0.0405   0.7639   0.7951
  -0.250   0.2012   0.01892   0.01204  -0.0402   0.7617   0.7963
   0.000   0.2264   0.01883   0.01191  -0.0401   0.7598   0.7977
   0.250   0.2523   0.01872   0.01177  -0.0402   0.7581   0.7993
   0.500   0.2687   0.01865   0.01171  -0.0386   0.7548   0.8017
   0.750   0.2796   0.01844   0.01150  -0.0363   0.7508   0.8058
   1.000   0.3018   0.01828   0.01132  -0.0359   0.7479   0.8073
   1.250   0.3292   0.01818   0.01122  -0.0361   0.7456   0.8080
   1.500   0.3589   0.01807   0.01109  -0.0367   0.7436   0.8088
   1.750   0.3743   0.01815   0.01123  -0.0347   0.7387   0.8101
   2.000   0.3966   0.01808   0.01119  -0.0341   0.7347   0.8111
   2.250   0.4246   0.01790   0.01101  -0.0345   0.7316   0.8120
   2.500   0.4563   0.01769   0.01078  -0.0356   0.7291   0.8128
   2.750   0.4676   0.01773   0.01092  -0.0329   0.7225   0.8149
   3.000   0.4941   0.01755   0.01076  -0.0330   0.7184   0.8162
   3.250   0.5262   0.01729   0.01050  -0.0342   0.7153   0.8171
   3.500   0.5400   0.01726   0.01054  -0.0322   0.7084   0.8189
   3.750   0.5680   0.01702   0.01033  -0.0327   0.7036   0.8200
   4.000   0.5926   0.01687   0.01022  -0.0325   0.6981   0.8211
   4.250   0.6121   0.01679   0.01023  -0.0311   0.6911   0.8220
   4.500   0.6402   0.01659   0.01009  -0.0313   0.6856   0.8227
   4.750   0.6557   0.01655   0.01014  -0.0292   0.6770   0.8237
   5.000   0.6768   0.01642   0.01008  -0.0282   0.6688   0.8246
   5.250   0.7002   0.01623   0.00995  -0.0275   0.6597   0.8254
   5.500   0.7140   0.01619   0.01000  -0.0252   0.6480   0.8266
   5.750   0.7291   0.01610   0.01000  -0.0230   0.6355   0.8278
   6.000   0.7440   0.01599   0.00994  -0.0208   0.6208   0.8290
   6.250   0.7621   0.01587   0.00984  -0.0192   0.6021   0.8304
   6.500   0.7814   0.01578   0.00972  -0.0178   0.5760   0.8319
   6.750   0.8008   0.01578   0.00959  -0.0164   0.5392   0.8331
   7.000   0.8138   0.01607   0.00966  -0.0141   0.4956   0.8343
   7.250   0.8190   0.01664   0.01004  -0.0106   0.4543   0.8353
   7.750   0.8251   0.01810   0.01121  -0.0034   0.3825   0.8376
   8.000   0.8286   0.01894   0.01193  -0.0003   0.3497   0.8387
   8.250   0.8324   0.01985   0.01271   0.0026   0.3171   0.8400
   8.500   0.8375   0.02079   0.01353   0.0052   0.2855   0.8413
   8.750   0.8427   0.02179   0.01442   0.0076   0.2538   0.8429
   9.000   0.8485   0.02285   0.01535   0.0097   0.2228   0.8443
   9.250   0.8545   0.02398   0.01632   0.0117   0.1912   0.8456
   9.500   0.8624   0.02507   0.01732   0.0133   0.1629   0.8468
   9.750   0.8721   0.02612   0.01828   0.0146   0.1390   0.8479
  10.000   0.8826   0.02714   0.01925   0.0159   0.1196   0.8489
  10.250   0.8920   0.02819   0.02025   0.0173   0.1009   0.8497
  10.500   0.9008   0.02931   0.02132   0.0187   0.0845   0.8507
  10.750   0.9104   0.03043   0.02242   0.0200   0.0706   0.8516
  11.000   0.9204   0.03156   0.02356   0.0211   0.0600   0.8526
  11.250   0.9309   0.03270   0.02475   0.0222   0.0514   0.8537
  11.500   0.9401   0.03397   0.02605   0.0233   0.0445   0.8548
  11.750   0.9488   0.03531   0.02745   0.0243   0.0381   0.8560
  12.000   0.9575   0.03668   0.02890   0.0253   0.0334   0.8574
  12.250   0.9662   0.03809   0.03038   0.0262   0.0294   0.8588
  12.500   0.9729   0.03972   0.03204   0.0271   0.0257   0.8601
  12.750   0.9827   0.04115   0.03360   0.0277   0.0230   0.8613
  13.000   0.9903   0.04279   0.03530   0.0283   0.0204   0.8624
  13.250   0.9937   0.04480   0.03738   0.0292   0.0181   0.8634
  13.500   1.0006   0.04651   0.03925   0.0298   0.0165   0.8644
  13.750   1.0072   0.04829   0.04115   0.0304   0.0145   0.8655
  14.000   1.0091   0.05060   0.04352   0.0309   0.0130   0.8666
  14.250   1.0116   0.05295   0.04601   0.0314   0.0119   0.8678
  14.500   1.0148   0.05532   0.04854   0.0316   0.0108   0.8690
  14.750   1.0166   0.05792   0.05132   0.0318   0.0101   0.8702
  15.000   1.0181   0.06066   0.05419   0.0317   0.0093   0.8715
  15.250   1.0177   0.06372   0.05737   0.0314   0.0087   0.8728
  15.500   1.0146   0.06720   0.06097   0.0309   0.0083   0.8740
  15.750   1.0124   0.07074   0.06467   0.0303   0.0078   0.8752
  16.000   1.0116   0.07425   0.06836   0.0294   0.0074   0.8764
  16.250   1.0090   0.07800   0.07230   0.0285   0.0070   0.8776
  16.500   1.0069   0.08179   0.07626   0.0273   0.0066   0.8789
  16.750   1.0048   0.08571   0.08033   0.0257   0.0062   0.8803
  17.000   0.9996   0.09026   0.08504   0.0239   0.0059   0.8817
  17.250   0.9942   0.09498   0.08991   0.0218   0.0057   0.8831
  17.500   0.9880   0.10005   0.09512   0.0193   0.0055   0.8846
  17.750   0.9790   0.10570   0.10093   0.0164   0.0054   0.8859
  18.000   0.9705   0.11143   0.10683   0.0135   0.0053   0.8871
  18.250   0.9592   0.11787   0.11341   0.0100   0.0052   0.8883
  18.500   0.9503   0.12402   0.11974   0.0065   0.0053   0.8895
  18.750   0.9397   0.13059   0.12647   0.0028   0.0052   0.8907
  19.000   0.9276   0.13761   0.13365  -0.0012   0.0052   0.8918
  19.250   0.9154   0.14487   0.14106  -0.0055   0.0051   0.8931
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