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EPPLER 562 AIRFOIL (e562-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 562 AIRFOIL (e562-il)
Reynolds number: 1,000,000
Max Cl/Cd: 115.05 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e562-il-1000000-n5.txt
Download as CSV file: xf-e562-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 562 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -17.000  -0.8138   0.10122   0.09827  -0.0502   1.0000   0.0059
 -16.750  -0.8337   0.09440   0.09137  -0.0535   1.0000   0.0060
 -16.500  -0.8457   0.08909   0.08597  -0.0559   1.0000   0.0059
 -16.250  -0.8634   0.08298   0.07977  -0.0589   1.0000   0.0059
 -16.000  -0.8801   0.07723   0.07394  -0.0616   1.0000   0.0060
 -15.750  -0.8949   0.07191   0.06854  -0.0640   1.0000   0.0060
 -15.500  -0.9124   0.06643   0.06297  -0.0665   1.0000   0.0061
 -15.250  -0.9279   0.06150   0.05796  -0.0686   1.0000   0.0060
 -15.000  -0.9457   0.05663   0.05301  -0.0704   1.0000   0.0060
 -14.750  -0.9663   0.05164   0.04794  -0.0722   1.0000   0.0061
 -14.500  -0.9832   0.04737   0.04357  -0.0734   1.0000   0.0061
 -14.250  -0.9978   0.04283   0.03894  -0.0757   0.9996   0.0062
 -14.000  -0.9922   0.03841   0.03442  -0.0814   0.9975   0.0063
 -13.750  -0.9824   0.03437   0.03028  -0.0872   0.9950   0.0064
 -13.500  -0.9740   0.03064   0.02644  -0.0923   0.9923   0.0065
 -13.250  -0.9645   0.02728   0.02299  -0.0969   0.9880   0.0067
 -13.000  -0.9371   0.02409   0.01966  -0.1046   0.9855   0.0068
 -12.750  -0.9074   0.02240   0.01787  -0.1087   0.9841   0.0070
 -12.500  -0.8875   0.02123   0.01663  -0.1096   0.9810   0.0072
 -12.250  -0.8650   0.02020   0.01553  -0.1104   0.9777   0.0074
 -12.000  -0.8370   0.01932   0.01458  -0.1120   0.9756   0.0077
 -11.750  -0.8074   0.01842   0.01361  -0.1138   0.9740   0.0079
 -11.500  -0.7763   0.01757   0.01272  -0.1158   0.9728   0.0084
 -11.250  -0.7586   0.01691   0.01203  -0.1147   0.9677   0.0087
 -11.000  -0.7316   0.01628   0.01136  -0.1153   0.9645   0.0092
 -10.750  -0.7014   0.01567   0.01071  -0.1165   0.9622   0.0096
 -10.500  -0.6696   0.01511   0.01009  -0.1180   0.9605   0.0101
 -10.250  -0.6521   0.01459   0.00954  -0.1164   0.9526   0.0105
 -10.000  -0.6227   0.01402   0.00895  -0.1172   0.9491   0.0111
  -9.750  -0.5981   0.01357   0.00847  -0.1170   0.9427   0.0118
  -9.500  -0.5685   0.01311   0.00796  -0.1176   0.9377   0.0125
  -9.250  -0.5341   0.01266   0.00747  -0.1193   0.9342   0.0131
  -9.000  -0.5019   0.01215   0.00694  -0.1205   0.9274   0.0141
  -8.750  -0.4617   0.01169   0.00645  -0.1234   0.9223   0.0152
  -8.500  -0.4176   0.01130   0.00600  -0.1270   0.9162   0.0163
  -8.250  -0.3669   0.01083   0.00549  -0.1322   0.9080   0.0179
  -8.000  -0.3170   0.01047   0.00506  -0.1372   0.8950   0.0195
  -7.750  -0.2775   0.01021   0.00469  -0.1398   0.8748   0.0212
  -7.500  -0.2472   0.01000   0.00438  -0.1405   0.8518   0.0236
  -7.250  -0.2206   0.00981   0.00410  -0.1403   0.8296   0.0272
  -6.750  -0.1702   0.00934   0.00354  -0.1396   0.7906   0.0467
  -6.500  -0.1449   0.00911   0.00329  -0.1392   0.7724   0.0601
  -6.250  -0.1194   0.00889   0.00305  -0.1388   0.7554   0.0749
  -6.000  -0.0936   0.00869   0.00285  -0.1385   0.7392   0.0906
  -5.750  -0.0673   0.00853   0.00266  -0.1383   0.7241   0.1055
  -5.500  -0.0410   0.00836   0.00249  -0.1381   0.7094   0.1223
  -5.250  -0.0145   0.00819   0.00233  -0.1379   0.6947   0.1427
  -5.000   0.0124   0.00802   0.00218  -0.1378   0.6810   0.1672
  -4.750   0.0396   0.00792   0.00207  -0.1376   0.6677   0.1832
  -4.500   0.0669   0.00783   0.00198  -0.1375   0.6549   0.1998
  -4.250   0.0942   0.00777   0.00190  -0.1374   0.6424   0.2145
  -4.000   0.1215   0.00772   0.00183  -0.1373   0.6301   0.2289
  -3.750   0.1492   0.00767   0.00177  -0.1372   0.6178   0.2448
  -3.500   0.1769   0.00764   0.00172  -0.1371   0.6064   0.2545
  -3.000   0.2321   0.00765   0.00165  -0.1369   0.5834   0.2705
  -2.750   0.2600   0.00767   0.00162  -0.1368   0.5730   0.2775
  -2.500   0.2877   0.00768   0.00160  -0.1367   0.5622   0.2858
  -2.250   0.3155   0.00769   0.00158  -0.1366   0.5516   0.2949
  -2.000   0.3434   0.00769   0.00158  -0.1366   0.5422   0.3070
  -1.750   0.3710   0.00773   0.00158  -0.1364   0.5322   0.3147
  -1.500   0.3990   0.00775   0.00158  -0.1364   0.5224   0.3215
  -1.250   0.4267   0.00780   0.00158  -0.1363   0.5134   0.3278
  -1.000   0.4545   0.00783   0.00160  -0.1362   0.5044   0.3360
  -0.750   0.4823   0.00788   0.00162  -0.1361   0.4959   0.3428
  -0.500   0.5099   0.00793   0.00165  -0.1360   0.4863   0.3500
  -0.250   0.5377   0.00798   0.00167  -0.1359   0.4786   0.3565
   0.000   0.5653   0.00803   0.00171  -0.1357   0.4701   0.3638
   0.250   0.5930   0.00809   0.00175  -0.1356   0.4621   0.3718
   0.500   0.6204   0.00815   0.00180  -0.1355   0.4539   0.3787
   0.750   0.6481   0.00821   0.00185  -0.1354   0.4468   0.3864
   1.000   0.6754   0.00829   0.00191  -0.1352   0.4384   0.3936
   1.250   0.7029   0.00835   0.00198  -0.1351   0.4313   0.4012
   1.500   0.7302   0.00844   0.00204  -0.1349   0.4231   0.4085
   1.750   0.7575   0.00851   0.00212  -0.1347   0.4163   0.4160
   2.000   0.7847   0.00860   0.00219  -0.1346   0.4090   0.4228
   2.250   0.8118   0.00868   0.00228  -0.1344   0.4021   0.4305
   2.500   0.8390   0.00876   0.00237  -0.1342   0.3954   0.4379
   3.000   0.8929   0.00895   0.00256  -0.1337   0.3820   0.4528
   3.250   0.9195   0.00906   0.00267  -0.1334   0.3752   0.4601
   3.500   0.9463   0.00916   0.00278  -0.1332   0.3693   0.4682
   3.750   0.9729   0.00927   0.00289  -0.1329   0.3622   0.4759
   4.000   0.9991   0.00939   0.00302  -0.1326   0.3558   0.4849
   4.250   1.0258   0.00949   0.00314  -0.1323   0.3495   0.4932
   4.500   1.0516   0.00964   0.00329  -0.1319   0.3420   0.5031
   4.750   1.0779   0.00975   0.00343  -0.1316   0.3354   0.5127
   5.250   1.1292   0.01003   0.00374  -0.1307   0.3204   0.5354
   5.500   1.1543   0.01020   0.00392  -0.1302   0.3116   0.5475
   5.750   1.1797   0.01034   0.00409  -0.1298   0.3043   0.5615
   6.000   1.2041   0.01054   0.00430  -0.1291   0.2951   0.5770
   6.250   1.2291   0.01070   0.00449  -0.1286   0.2868   0.5937
   6.500   1.2531   0.01091   0.00471  -0.1279   0.2776   0.6122
   6.750   1.2771   0.01110   0.00494  -0.1272   0.2677   0.6350
   7.000   1.3004   0.01132   0.00519  -0.1264   0.2566   0.6586
   7.500   1.3447   0.01182   0.00576  -0.1244   0.2344   0.7213
   7.750   1.3658   0.01204   0.00605  -0.1232   0.2231   0.7620
   8.000   1.3854   0.01226   0.00637  -0.1217   0.2128   0.8175
   8.250   1.3972   0.01232   0.00665  -0.1184   0.2022   0.9796
   8.500   1.4153   0.01272   0.00700  -0.1167   0.1896   1.0000
   8.750   1.4328   0.01319   0.00740  -0.1149   0.1748   1.0000
   9.000   1.4485   0.01375   0.00786  -0.1129   0.1564   1.0000
   9.250   1.4619   0.01440   0.00840  -0.1105   0.1371   1.0000
   9.500   1.4764   0.01499   0.00892  -0.1083   0.1232   1.0000
   9.750   1.4917   0.01554   0.00943  -0.1063   0.1122   1.0000
  10.000   1.5058   0.01615   0.00998  -0.1042   0.1016   1.0000
  10.250   1.5190   0.01679   0.01058  -0.1019   0.0917   1.0000
  10.500   1.5307   0.01751   0.01125  -0.0995   0.0813   1.0000
  10.750   1.5415   0.01828   0.01198  -0.0970   0.0715   1.0000
  11.000   1.5521   0.01907   0.01274  -0.0946   0.0631   1.0000
  11.250   1.5603   0.02001   0.01364  -0.0920   0.0539   1.0000
  11.500   1.5697   0.02090   0.01452  -0.0896   0.0476   1.0000
  11.750   1.5777   0.02191   0.01552  -0.0872   0.0420   1.0000
  12.000   1.5873   0.02285   0.01648  -0.0851   0.0381   1.0000
  12.250   1.5946   0.02398   0.01761  -0.0828   0.0342   1.0000
  12.500   1.6023   0.02513   0.01879  -0.0808   0.0308   1.0000
  12.750   1.6082   0.02645   0.02014  -0.0787   0.0275   1.0000
  13.000   1.6139   0.02786   0.02157  -0.0768   0.0247   1.0000
  13.250   1.6188   0.02941   0.02315  -0.0750   0.0221   1.0000
  13.500   1.6224   0.03113   0.02490  -0.0733   0.0197   1.0000
  13.750   1.6273   0.03284   0.02666  -0.0719   0.0183   1.0000
  14.000   1.6311   0.03473   0.02859  -0.0706   0.0168   1.0000
  14.250   1.6331   0.03687   0.03079  -0.0694   0.0154   1.0000
  14.500   1.6367   0.03897   0.03295  -0.0685   0.0145   1.0000
  14.750   1.6386   0.04132   0.03537  -0.0677   0.0135   1.0000
  15.000   1.6390   0.04393   0.03804  -0.0671   0.0126   1.0000
  15.250   1.6400   0.04658   0.04076  -0.0666   0.0119   1.0000
  15.500   1.6404   0.04938   0.04364  -0.0663   0.0113   1.0000
  15.750   1.6391   0.05250   0.04682  -0.0662   0.0106   1.0000
  16.000   1.6368   0.05584   0.05024  -0.0663   0.0100   1.0000
  16.250   1.6348   0.05924   0.05372  -0.0665   0.0096   1.0000
  16.500   1.6327   0.06276   0.05732  -0.0669   0.0091   1.0000
  16.750   1.6294   0.06655   0.06120  -0.0675   0.0087   1.0000
  17.000   1.6251   0.07057   0.06531  -0.0683   0.0083   1.0000
  17.250   1.6192   0.07491   0.06973  -0.0693   0.0079   1.0000
  17.500   1.6135   0.07933   0.07425  -0.0704   0.0075   1.0000
  17.750   1.6088   0.08369   0.07870  -0.0716   0.0072   1.0000
  18.000   1.6032   0.08827   0.08337  -0.0730   0.0069   1.0000
  18.250   1.5969   0.09302   0.08822  -0.0746   0.0066   1.0000
  18.500   1.5896   0.09801   0.09329  -0.0764   0.0062   1.0000
  18.750   1.5817   0.10318   0.09855  -0.0783   0.0059   1.0000
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