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EPPLER 548 AIRFOIL (e548-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 548 AIRFOIL (e548-il)
Reynolds number: 200,000
Max Cl/Cd: 63.42 at α=9.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e548-il-200000-n5.txt
Download as CSV file: xf-e548-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 548 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
  ------ -------- --------- --------- -------- -------- --------
 -13.250  -0.6139   0.07247   0.06827  -0.0571   1.0000   0.0082
 -13.000  -0.6534   0.06389   0.05931  -0.0603   1.0000   0.0080
 -12.750  -0.6752   0.05875   0.05393  -0.0611   1.0000   0.0080
 -12.500  -0.6892   0.05496   0.04997  -0.0610   1.0000   0.0080
 -12.250  -0.7040   0.05117   0.04592  -0.0603   1.0000   0.0080
 -12.000  -0.7109   0.04852   0.04315  -0.0594   1.0000   0.0081
 -11.750  -0.7203   0.04545   0.03983  -0.0578   1.0000   0.0080
 -11.500  -0.7218   0.04360   0.03792  -0.0564   1.0000   0.0083
 -11.250  -0.7251   0.04121   0.03531  -0.0545   1.0000   0.0083
 -11.000  -0.7247   0.03936   0.03332  -0.0526   1.0000   0.0084
 -10.750  -0.7231   0.03758   0.03139  -0.0505   1.0000   0.0085
 -10.500  -0.7189   0.03579   0.02941  -0.0484   1.0000   0.0085
 -10.250  -0.7137   0.03431   0.02779  -0.0463   1.0000   0.0088
 -10.000  -0.7004   0.03263   0.02595  -0.0452   0.9931   0.0089
  -9.750  -0.6651   0.03050   0.02357  -0.0481   0.9470   0.0093
  -9.500  -0.6061   0.02833   0.02100  -0.0553   0.9095   0.0102
  -9.250  -0.5504   0.02674   0.01920  -0.0623   0.8648   0.0110
  -8.750  -0.4895   0.02479   0.01673  -0.0651   0.7974   0.0129
  -8.500  -0.4714   0.02396   0.01578  -0.0643   0.7743   0.0133
  -8.250  -0.4554   0.02323   0.01493  -0.0630   0.7548   0.0137
  -8.000  -0.4401   0.02250   0.01408  -0.0615   0.7377   0.0146
  -7.750  -0.4257   0.02179   0.01320  -0.0598   0.7223   0.0157
  -7.500  -0.4122   0.02108   0.01240  -0.0581   0.7085   0.0170
  -7.250  -0.3975   0.02050   0.01172  -0.0564   0.6953   0.0186
  -7.000  -0.3838   0.01989   0.01103  -0.0546   0.6837   0.0205
  -6.750  -0.3704   0.01932   0.01038  -0.0527   0.6736   0.0237
  -6.500  -0.3583   0.01875   0.00975  -0.0505   0.6638   0.0277
  -6.250  -0.3475   0.01826   0.00921  -0.0480   0.6552   0.0333
  -6.000  -0.3358   0.01773   0.00870  -0.0457   0.6467   0.0437
  -5.750  -0.3228   0.01719   0.00819  -0.0436   0.6392   0.0607
  -5.500  -0.3092   0.01664   0.00773  -0.0416   0.6313   0.0862
  -5.000  -0.2872   0.01518   0.00674  -0.0371   0.6174   0.1947
  -4.750  -0.2827   0.01400   0.00609  -0.0341   0.6112   0.3102
  -4.500  -0.2823   0.01261   0.00569  -0.0300   0.6060   0.5045
  -4.250  -0.2586   0.01308   0.00651  -0.0283   0.5999   0.6126
  -4.000  -0.2329   0.01325   0.00650  -0.0278   0.5944   0.6391
  -3.750  -0.2062   0.01358   0.00670  -0.0273   0.5893   0.6565
  -3.500  -0.1793   0.01403   0.00707  -0.0266   0.5837   0.6726
  -3.250  -0.1526   0.01462   0.00756  -0.0257   0.5785   0.6879
  -3.000  -0.1255   0.01531   0.00817  -0.0246   0.5739   0.7013
  -2.750  -0.0974   0.01571   0.00853  -0.0240   0.5688   0.7068
  -2.500  -0.0701   0.01572   0.00844  -0.0239   0.5644   0.7092
  -2.250  -0.0432   0.01567   0.00825  -0.0239   0.5605   0.7117
  -2.000  -0.0163   0.01556   0.00802  -0.0241   0.5569   0.7142
  -1.750   0.0105   0.01540   0.00776  -0.0243   0.5526   0.7170
  -1.500   0.0375   0.01525   0.00749  -0.0246   0.5485   0.7194
  -1.250   0.0650   0.01524   0.00738  -0.0247   0.5448   0.7205
  -1.000   0.0926   0.01523   0.00728  -0.0248   0.5416   0.7217
  -0.750   0.1202   0.01519   0.00720  -0.0249   0.5380   0.7228
  -0.500   0.1477   0.01517   0.00714  -0.0251   0.5345   0.7241
  -0.250   0.1753   0.01515   0.00707  -0.0252   0.5313   0.7257
   0.000   0.2030   0.01514   0.00698  -0.0255   0.5282   0.7272
   0.250   0.2309   0.01514   0.00688  -0.0258   0.5254   0.7286
   0.500   0.2585   0.01510   0.00683  -0.0260   0.5219   0.7301
   0.750   0.2863   0.01508   0.00678  -0.0264   0.5187   0.7318
   1.000   0.3143   0.01507   0.00673  -0.0268   0.5158   0.7338
   1.250   0.3425   0.01506   0.00666  -0.0272   0.5130   0.7355
   1.500   0.3704   0.01510   0.00664  -0.0275   0.5104   0.7364
   1.750   0.3979   0.01514   0.00669  -0.0276   0.5076   0.7373
   2.000   0.4253   0.01518   0.00676  -0.0278   0.5045   0.7383
   2.250   0.4528   0.01523   0.00683  -0.0280   0.5016   0.7394
   2.500   0.4803   0.01528   0.00690  -0.0282   0.4987   0.7406
   2.750   0.5080   0.01535   0.00695  -0.0284   0.4960   0.7420
   3.000   0.5360   0.01544   0.00701  -0.0287   0.4937   0.7436
   3.250   0.5633   0.01552   0.00715  -0.0289   0.4909   0.7451
   3.500   0.5905   0.01560   0.00727  -0.0291   0.4877   0.7466
   3.750   0.6179   0.01567   0.00737  -0.0293   0.4845   0.7481
   4.000   0.6456   0.01575   0.00747  -0.0296   0.4816   0.7496
   4.250   0.6736   0.01584   0.00754  -0.0300   0.4789   0.7511
   4.500   0.7014   0.01595   0.00766  -0.0303   0.4761   0.7524
   4.750   0.7272   0.01605   0.00788  -0.0302   0.4724   0.7535
   5.000   0.7533   0.01615   0.00806  -0.0302   0.4686   0.7548
   5.250   0.7798   0.01624   0.00820  -0.0302   0.4649   0.7562
   5.500   0.8070   0.01634   0.00832  -0.0303   0.4616   0.7579
   5.750   0.8323   0.01646   0.00855  -0.0301   0.4574   0.7596
   6.000   0.8578   0.01657   0.00877  -0.0300   0.4528   0.7612
   6.250   0.8839   0.01666   0.00891  -0.0300   0.4486   0.7629
   6.500   0.9110   0.01676   0.00900  -0.0301   0.4446   0.7646
   6.750   0.9349   0.01688   0.00929  -0.0298   0.4388   0.7665
   7.000   0.9601   0.01697   0.00945  -0.0297   0.4334   0.7683
   7.250   0.9855   0.01705   0.00956  -0.0295   0.4286   0.7697
   7.500   1.0078   0.01718   0.00988  -0.0288   0.4219   0.7713
   7.750   1.0315   0.01727   0.01004  -0.0283   0.4156   0.7730
   8.000   1.0540   0.01740   0.01030  -0.0277   0.4086   0.7751
   8.250   1.0762   0.01752   0.01052  -0.0269   0.4006   0.7774
   8.500   1.0977   0.01767   0.01078  -0.0262   0.3919   0.7799
   8.750   1.1185   0.01781   0.01096  -0.0253   0.3826   0.7823
   9.000   1.1382   0.01801   0.01128  -0.0243   0.3711   0.7847
   9.250   1.1555   0.01822   0.01160  -0.0228   0.3584   0.7867
   9.500   1.1706   0.01849   0.01192  -0.0210   0.3437   0.7889
   9.750   1.1821   0.01885   0.01230  -0.0186   0.3266   0.7916
  10.000   1.1872   0.01931   0.01274  -0.0153   0.3086   0.7946
  10.250   1.1902   0.02000   0.01340  -0.0119   0.2892   0.7980
  10.500   1.1906   0.02091   0.01427  -0.0085   0.2694   0.8015
  10.750   1.1881   0.02199   0.01535  -0.0051   0.2519   0.8048
  11.000   1.1834   0.02336   0.01670  -0.0019   0.2350   0.8090
  11.250   1.1784   0.02497   0.01830   0.0007   0.2195   0.8137
  11.500   1.1738   0.02679   0.02013   0.0029   0.2050   0.8184
  11.750   1.1689   0.02878   0.02215   0.0047   0.1916   0.8229
  12.000   1.1642   0.03100   0.02440   0.0060   0.1786   0.8281
  12.500   1.1544   0.03591   0.02935   0.0079   0.1552   0.8390
  12.750   1.1492   0.03856   0.03202   0.0085   0.1447   0.8457
  13.000   1.1461   0.04110   0.03462   0.0090   0.1340   0.8528
  13.250   1.1430   0.04369   0.03727   0.0093   0.1247   0.8617
  13.500   1.1382   0.04651   0.04014   0.0096   0.1160   0.8723
  13.750   1.1363   0.04913   0.04285   0.0097   0.1074   0.8878
  14.000   1.1358   0.05190   0.04573   0.0092   0.0993   0.9168
  14.500   1.1331   0.05770   0.05162   0.0080   0.0845   1.0000
  14.750   1.1316   0.06083   0.05477   0.0074   0.0783   1.0000
  15.000   1.1317   0.06386   0.05782   0.0066   0.0720   1.0000
  15.250   1.1309   0.06704   0.06103   0.0058   0.0665   1.0000
  15.500   1.1299   0.07031   0.06433   0.0050   0.0611   1.0000
  15.750   1.1297   0.07352   0.06759   0.0041   0.0564   1.0000
  16.000   1.1282   0.07699   0.07109   0.0030   0.0519   1.0000
  16.250   1.1278   0.08036   0.07451   0.0019   0.0480   1.0000
  16.500   1.1264   0.08394   0.07815   0.0007   0.0443   1.0000
  16.750   1.1248   0.08761   0.08187  -0.0006   0.0414   1.0000
  17.000   1.1242   0.09120   0.08554  -0.0019   0.0383   1.0000
  17.250   1.1203   0.09532   0.08969  -0.0035   0.0360   1.0000
  17.500   1.1204   0.09891   0.09339  -0.0049   0.0336   1.0000
  17.750   1.1180   0.10295   0.09750  -0.0066   0.0314   1.0000
  18.000   1.1144   0.10723   0.10182  -0.0085   0.0296   1.0000
  18.250   1.1136   0.11111   0.10582  -0.0102   0.0277   1.0000
  18.500   1.1099   0.11551   0.11029  -0.0123   0.0261   1.0000
  18.750   1.1058   0.12001   0.11485  -0.0145   0.0249   1.0000
  19.000   1.1045   0.12412   0.11909  -0.0165   0.0233   1.0000
  19.250   1.1016   0.12854   0.12360  -0.0188   0.0221   1.0000
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