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EPPLER 562 AIRFOIL (e562-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 562 AIRFOIL (e562-il)
Reynolds number: 200,000
Max Cl/Cd: 73.76 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e562-il-200000.txt
Download as CSV file: xf-e562-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.6504   0.06640   0.06210  -0.0750   1.0000   0.0300
 -12.000  -0.6832   0.06025   0.05574  -0.0788   1.0000   0.0298
 -11.750  -0.7053   0.05656   0.05191  -0.0806   1.0000   0.0295
 -11.500  -0.7295   0.05308   0.04831  -0.0808   1.0000   0.0295
 -11.250  -0.7531   0.05095   0.04609  -0.0791   1.0000   0.0294
 -11.000  -0.7715   0.04828   0.04330  -0.0780   1.0000   0.0293
 -10.750  -0.7845   0.04558   0.04039  -0.0769   1.0000   0.0294
 -10.500  -0.7911   0.04251   0.03712  -0.0757   1.0000   0.0295
 -10.250  -0.7900   0.03963   0.03416  -0.0746   1.0000   0.0301
 -10.000  -0.7833   0.03791   0.03241  -0.0735   1.0000   0.0309
  -9.750  -0.7744   0.03640   0.03082  -0.0725   1.0000   0.0317
  -9.500  -0.7644   0.03473   0.02900  -0.0717   1.0000   0.0325
  -9.250  -0.7528   0.03294   0.02700  -0.0710   1.0000   0.0333
  -9.000  -0.7322   0.03112   0.02492  -0.0716   0.9988   0.0342
  -8.750  -0.6937   0.02943   0.02288  -0.0751   0.9946   0.0354
  -8.500  -0.6612   0.02728   0.02078  -0.0774   0.9904   0.0372
  -8.250  -0.6231   0.02615   0.01959  -0.0806   0.9858   0.0400
  -8.000  -0.5857   0.02498   0.01826  -0.0833   0.9811   0.0428
  -7.750  -0.5507   0.02350   0.01684  -0.0859   0.9758   0.0462
  -7.500  -0.5086   0.02256   0.01577  -0.0894   0.9723   0.0509
  -7.250  -0.4763   0.02118   0.01446  -0.0915   0.9652   0.0571
  -7.000  -0.4346   0.01991   0.01318  -0.0952   0.9614   0.0679
  -6.750  -0.3995   0.01851   0.01189  -0.0978   0.9547   0.0945
  -6.500  -0.3590   0.01717   0.01084  -0.1015   0.9503   0.1505
  -6.250  -0.3201   0.01659   0.01036  -0.1042   0.9449   0.1915
  -6.000  -0.2828   0.01621   0.00998  -0.1062   0.9382   0.2208
  -5.750  -0.2390   0.01590   0.00962  -0.1094   0.9346   0.2471
  -5.500  -0.2064   0.01570   0.00940  -0.1103   0.9258   0.2679
  -5.250  -0.1635   0.01552   0.00912  -0.1131   0.9216   0.2914
  -5.000  -0.1274   0.01530   0.00886  -0.1145   0.9146   0.3076
  -4.750  -0.0886   0.01499   0.00854  -0.1164   0.9089   0.3219
  -4.500  -0.0449   0.01464   0.00817  -0.1192   0.9057   0.3364
  -4.250  -0.0106   0.01436   0.00788  -0.1202   0.8970   0.3477
  -4.000   0.0333   0.01400   0.00746  -0.1230   0.8920   0.3602
  -3.750   0.0757   0.01374   0.00710  -0.1257   0.8850   0.3728
  -3.500   0.1170   0.01346   0.00685  -0.1280   0.8766   0.3838
  -3.250   0.1568   0.01324   0.00660  -0.1301   0.8665   0.3953
  -3.000   0.2015   0.01301   0.00627  -0.1332   0.8575   0.4078
  -2.750   0.2362   0.01289   0.00611  -0.1343   0.8437   0.4174
  -2.500   0.2704   0.01276   0.00592  -0.1354   0.8295   0.4269
  -2.250   0.3036   0.01272   0.00576  -0.1362   0.8150   0.4375
  -2.000   0.3349   0.01265   0.00566  -0.1366   0.8003   0.4458
  -1.750   0.3656   0.01264   0.00552  -0.1370   0.7857   0.4562
  -1.500   0.3948   0.01263   0.00549  -0.1370   0.7712   0.4649
  -1.250   0.4239   0.01264   0.00539  -0.1371   0.7570   0.4746
  -1.000   0.4525   0.01267   0.00536  -0.1370   0.7432   0.4840
  -0.750   0.4795   0.01270   0.00533  -0.1366   0.7289   0.4934
  -0.500   0.5062   0.01275   0.00532  -0.1362   0.7148   0.5036
  -0.250   0.5328   0.01278   0.00533  -0.1358   0.7013   0.5126
   0.000   0.5601   0.01286   0.00532  -0.1356   0.6884   0.5234
   0.250   0.5873   0.01292   0.00536  -0.1352   0.6763   0.5330
   0.500   0.6139   0.01298   0.00538  -0.1348   0.6638   0.5433
   0.750   0.6400   0.01307   0.00544  -0.1344   0.6512   0.5545
   1.000   0.6664   0.01314   0.00551  -0.1339   0.6396   0.5647
   1.250   0.6938   0.01324   0.00556  -0.1337   0.6289   0.5762
   1.500   0.7195   0.01333   0.00565  -0.1332   0.6170   0.5886
   1.750   0.7453   0.01342   0.00577  -0.1327   0.6061   0.6002
   2.000   0.7724   0.01354   0.00585  -0.1324   0.5962   0.6130
   2.250   0.7975   0.01362   0.00599  -0.1318   0.5851   0.6266
   2.500   0.8236   0.01374   0.00613  -0.1314   0.5751   0.6415
   2.750   0.8500   0.01387   0.00625  -0.1310   0.5656   0.6576
   3.000   0.8747   0.01396   0.00645  -0.1303   0.5554   0.6748
   3.250   0.9009   0.01410   0.00660  -0.1298   0.5466   0.6943
   3.500   0.9248   0.01419   0.00679  -0.1289   0.5368   0.7168
   3.750   0.9493   0.01431   0.00699  -0.1281   0.5282   0.7427
   4.000   0.9722   0.01439   0.00718  -0.1269   0.5193   0.7748
   4.250   0.9931   0.01447   0.00738  -0.1253   0.5110   0.8170
   4.500   1.0083   0.01440   0.00747  -0.1222   0.5030   0.8854
   4.750   1.0353   0.01447   0.00758  -0.1220   0.4946   1.0000
   5.000   1.0633   0.01474   0.00778  -0.1222   0.4860   1.0000
   5.250   1.0898   0.01503   0.00805  -0.1221   0.4775   1.0000
   5.500   1.1166   0.01532   0.00828  -0.1220   0.4693   1.0000
   5.750   1.1419   0.01562   0.00860  -0.1216   0.4608   1.0000
   6.000   1.1681   0.01591   0.00884  -0.1214   0.4529   1.0000
   6.250   1.1923   0.01622   0.00919  -0.1207   0.4444   1.0000
   6.500   1.2181   0.01653   0.00945  -0.1204   0.4365   1.0000
   6.750   1.2410   0.01683   0.00982  -0.1195   0.4277   1.0000
   7.000   1.2665   0.01717   0.01010  -0.1192   0.4197   1.0000
   7.250   1.2879   0.01746   0.01048  -0.1180   0.4106   1.0000
   7.500   1.3129   0.01782   0.01077  -0.1175   0.4026   1.0000
   7.750   1.3327   0.01810   0.01117  -0.1161   0.3933   1.0000
   8.000   1.3555   0.01846   0.01151  -0.1153   0.3849   1.0000
   8.250   1.3750   0.01876   0.01188  -0.1138   0.3755   1.0000
   8.500   1.3953   0.01912   0.01228  -0.1125   0.3664   1.0000
   8.750   1.4148   0.01946   0.01263  -0.1110   0.3572   1.0000
   9.000   1.4318   0.01982   0.01308  -0.1092   0.3474   1.0000
   9.250   1.4501   0.02022   0.01346  -0.1076   0.3382   1.0000
   9.500   1.4640   0.02057   0.01391  -0.1052   0.3281   1.0000
   9.750   1.4774   0.02099   0.01438  -0.1027   0.3184   1.0000
  10.000   1.4906   0.02147   0.01483  -0.1003   0.3088   1.0000
  10.250   1.5008   0.02192   0.01542  -0.0974   0.2980   1.0000
  10.500   1.5112   0.02248   0.01602  -0.0947   0.2873   1.0000
  10.750   1.5200   0.02313   0.01666  -0.0919   0.2764   1.0000
  11.000   1.5276   0.02382   0.01741  -0.0890   0.2645   1.0000
  11.250   1.5347   0.02461   0.01828  -0.0862   0.2519   1.0000
  11.500   1.5402   0.02555   0.01925  -0.0833   0.2391   1.0000
  11.750   1.5445   0.02663   0.02037  -0.0805   0.2262   1.0000
  12.000   1.5471   0.02791   0.02165  -0.0778   0.2131   1.0000
  12.250   1.5481   0.02939   0.02314  -0.0752   0.1999   1.0000
  12.500   1.5476   0.03110   0.02486  -0.0727   0.1867   1.0000
  12.750   1.5453   0.03308   0.02683  -0.0703   0.1737   1.0000
  13.000   1.5427   0.03526   0.02903  -0.0683   0.1608   1.0000
  13.250   1.5393   0.03768   0.03148  -0.0666   0.1484   1.0000
  13.500   1.5346   0.04036   0.03419  -0.0651   0.1369   1.0000
  13.750   1.5284   0.04336   0.03721  -0.0640   0.1266   1.0000
  14.000   1.5194   0.04682   0.04066  -0.0630   0.1178   1.0000
  14.250   1.5126   0.05026   0.04415  -0.0625   0.1087   1.0000
  14.500   1.5052   0.05395   0.04789  -0.0622   0.1006   1.0000
  14.750   1.4939   0.05823   0.05217  -0.0623   0.0942   1.0000
  15.000   1.4876   0.06213   0.05617  -0.0625   0.0870   1.0000
  15.250   1.4749   0.06694   0.06096  -0.0631   0.0817   1.0000
  15.500   1.4693   0.07105   0.06520  -0.0637   0.0755   1.0000
  15.750   1.4574   0.07609   0.07023  -0.0648   0.0709   1.0000
  16.000   1.4508   0.08056   0.07482  -0.0658   0.0658   1.0000
  16.250   1.4418   0.08548   0.07978  -0.0671   0.0617   1.0000
  16.500   1.4331   0.09035   0.08469  -0.0684   0.0578   1.0000
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