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EPPLER 559 AIRFOIL (e559-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 559 AIRFOIL (e559-il)
Reynolds number: 500,000
Max Cl/Cd: 101.88 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e559-il-500000-n5.txt
Download as CSV file: xf-e559-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 559 AIRFOIL                              
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -15.750  -0.7389   0.08946   0.08562  -0.0585   1.0000   0.0131
 -15.500  -0.7441   0.08543   0.08153  -0.0602   1.0000   0.0132
 -15.250  -0.7495   0.08145   0.07749  -0.0618   1.0000   0.0134
 -15.000  -0.7556   0.07749   0.07348  -0.0634   1.0000   0.0135
 -14.750  -0.7612   0.07362   0.06954  -0.0649   1.0000   0.0137
 -14.500  -0.7675   0.06983   0.06569  -0.0663   1.0000   0.0139
 -14.250  -0.7751   0.06600   0.06180  -0.0677   1.0000   0.0139
 -14.000  -0.7829   0.06232   0.05806  -0.0689   1.0000   0.0140
 -13.750  -0.7936   0.05858   0.05427  -0.0700   1.0000   0.0141
 -13.500  -0.8047   0.05495   0.05058  -0.0708   1.0000   0.0142
 -13.250  -0.8183   0.05129   0.04685  -0.0715   1.0000   0.0142
 -13.000  -0.8358   0.04747   0.04298  -0.0720   1.0000   0.0143
 -12.750  -0.8508   0.04337   0.03882  -0.0736   0.9993   0.0144
 -12.500  -0.8472   0.03836   0.03371  -0.0804   0.9953   0.0146
 -12.250  -0.8438   0.03364   0.02888  -0.0867   0.9897   0.0149
 -12.000  -0.8253   0.02884   0.02392  -0.0958   0.9844   0.0151
 -11.750  -0.8030   0.02552   0.02046  -0.1023   0.9786   0.0155
 -11.500  -0.7773   0.02385   0.01867  -0.1053   0.9740   0.0160
 -11.250  -0.7475   0.02249   0.01722  -0.1082   0.9708   0.0166
 -11.000  -0.7283   0.02142   0.01605  -0.1083   0.9630   0.0171
 -10.500  -0.6789   0.01923   0.01372  -0.1103   0.9497   0.0183
 -10.250  -0.6514   0.01831   0.01274  -0.1114   0.9436   0.0189
 -10.000  -0.6253   0.01753   0.01189  -0.1119   0.9356   0.0196
  -9.750  -0.5930   0.01679   0.01106  -0.1135   0.9306   0.0205
  -9.500  -0.5624   0.01606   0.01027  -0.1147   0.9223   0.0215
  -9.250  -0.5245   0.01526   0.00941  -0.1175   0.9170   0.0229
  -9.000  -0.4862   0.01462   0.00870  -0.1201   0.9086   0.0245
  -8.750  -0.4385   0.01391   0.00793  -0.1247   0.9015   0.0272
  -8.500  -0.3919   0.01326   0.00723  -0.1291   0.8900   0.0324
  -8.250  -0.3487   0.01261   0.00656  -0.1329   0.8744   0.0434
  -8.000  -0.3124   0.01211   0.00601  -0.1350   0.8555   0.0562
  -7.750  -0.2814   0.01172   0.00557  -0.1360   0.8353   0.0686
  -7.500  -0.2538   0.01139   0.00518  -0.1362   0.8162   0.0818
  -7.250  -0.2271   0.01111   0.00486  -0.1361   0.7975   0.0950
  -7.000  -0.2008   0.01088   0.00458  -0.1359   0.7800   0.1077
  -6.750  -0.1746   0.01068   0.00433  -0.1356   0.7635   0.1195
  -6.500  -0.1484   0.01050   0.00409  -0.1354   0.7477   0.1327
  -6.250  -0.1221   0.01032   0.00388  -0.1351   0.7329   0.1476
  -6.000  -0.0956   0.01019   0.00371  -0.1348   0.7183   0.1601
  -5.750  -0.0688   0.01008   0.00355  -0.1346   0.7044   0.1727
  -5.500  -0.0420   0.00997   0.00340  -0.1344   0.6915   0.1841
  -5.250  -0.0151   0.00989   0.00327  -0.1341   0.6787   0.1948
  -4.750   0.0392   0.00977   0.00306  -0.1337   0.6543   0.2163
  -4.500   0.0664   0.00972   0.00297  -0.1335   0.6427   0.2251
  -4.250   0.0936   0.00971   0.00287  -0.1333   0.6311   0.2329
  -4.000   0.1211   0.00967   0.00280  -0.1331   0.6202   0.2403
  -3.750   0.1486   0.00966   0.00273  -0.1329   0.6100   0.2476
  -3.250   0.2036   0.00964   0.00261  -0.1326   0.5889   0.2614
  -3.000   0.2310   0.00965   0.00256  -0.1324   0.5798   0.2680
  -2.750   0.2587   0.00964   0.00253  -0.1322   0.5699   0.2752
  -2.500   0.2862   0.00967   0.00249  -0.1320   0.5607   0.2821
  -2.250   0.3137   0.00967   0.00247  -0.1319   0.5510   0.2888
  -2.000   0.3414   0.00969   0.00246  -0.1317   0.5427   0.2957
  -1.750   0.3689   0.00972   0.00244  -0.1315   0.5339   0.3022
  -1.500   0.3966   0.00974   0.00245  -0.1314   0.5254   0.3090
  -1.250   0.4239   0.00980   0.00245  -0.1312   0.5166   0.3154
  -1.000   0.4516   0.00982   0.00246  -0.1310   0.5091   0.3225
  -0.750   0.4790   0.00987   0.00248  -0.1308   0.5012   0.3291
  -0.500   0.5066   0.00992   0.00250  -0.1307   0.4939   0.3355
  -0.250   0.5339   0.00996   0.00254  -0.1305   0.4856   0.3428
   0.000   0.5612   0.01004   0.00257  -0.1303   0.4788   0.3495
   0.250   0.5888   0.01007   0.00262  -0.1301   0.4719   0.3561
   0.500   0.6157   0.01016   0.00267  -0.1299   0.4650   0.3638
   0.750   0.6433   0.01021   0.00273  -0.1297   0.4581   0.3705
   1.000   0.6703   0.01029   0.00279  -0.1295   0.4512   0.3777
   1.250   0.6975   0.01037   0.00286  -0.1293   0.4455   0.3851
   1.500   0.7248   0.01043   0.00294  -0.1291   0.4393   0.3930
   1.750   0.7513   0.01054   0.00303  -0.1287   0.4329   0.4003
   2.000   0.7786   0.01060   0.00312  -0.1286   0.4271   0.4081
   2.250   0.8055   0.01069   0.00321  -0.1283   0.4212   0.4167
   2.500   0.8318   0.01080   0.00332  -0.1280   0.4159   0.4251
   2.750   0.8590   0.01088   0.00342  -0.1278   0.4108   0.4339
   3.000   0.8856   0.01097   0.00355  -0.1275   0.4049   0.4434
   3.500   0.9384   0.01118   0.00381  -0.1268   0.3950   0.4642
   3.750   0.9648   0.01128   0.00394  -0.1265   0.3899   0.4754
   4.250   1.0167   0.01152   0.00425  -0.1257   0.3799   0.5027
   4.500   1.0429   0.01162   0.00441  -0.1254   0.3750   0.5177
   4.750   1.0682   0.01176   0.00459  -0.1249   0.3700   0.5357
   5.000   1.0936   0.01189   0.00478  -0.1244   0.3654   0.5555
   5.250   1.1195   0.01199   0.00496  -0.1241   0.3604   0.5777
   5.500   1.1444   0.01211   0.00516  -0.1235   0.3553   0.6047
   5.750   1.1686   0.01226   0.00539  -0.1229   0.3503   0.6355
   6.000   1.1939   0.01234   0.00561  -0.1224   0.3457   0.6722
   6.250   1.2179   0.01244   0.00584  -0.1217   0.3405   0.7176
   6.500   1.2397   0.01256   0.00610  -0.1205   0.3354   0.7756
   7.000   1.2786   0.01255   0.00646  -0.1168   0.3259   1.0000
   7.250   1.3004   0.01280   0.00670  -0.1158   0.3204   1.0000
   7.500   1.3232   0.01302   0.00694  -0.1149   0.3154   1.0000
   7.750   1.3453   0.01326   0.00718  -0.1138   0.3093   1.0000
   8.000   1.3653   0.01357   0.00747  -0.1125   0.3036   1.0000
   8.250   1.3875   0.01381   0.00774  -0.1115   0.2975   1.0000
   8.500   1.4075   0.01412   0.00804  -0.1101   0.2907   1.0000
   8.750   1.4278   0.01443   0.00836  -0.1089   0.2844   1.0000
   9.000   1.4473   0.01476   0.00870  -0.1075   0.2768   1.0000
   9.250   1.4657   0.01513   0.00907  -0.1060   0.2696   1.0000
   9.500   1.4844   0.01550   0.00945  -0.1045   0.2617   1.0000
   9.750   1.5015   0.01594   0.00988  -0.1029   0.2536   1.0000
  10.000   1.5177   0.01642   0.01035  -0.1011   0.2443   1.0000
  10.250   1.5340   0.01690   0.01084  -0.0994   0.2357   1.0000
  10.500   1.5475   0.01751   0.01142  -0.0973   0.2260   1.0000
  10.750   1.5608   0.01814   0.01204  -0.0953   0.2147   1.0000
  11.000   1.5725   0.01887   0.01275  -0.0931   0.2032   1.0000
  11.250   1.5819   0.01973   0.01358  -0.0907   0.1911   1.0000
  11.500   1.5901   0.02068   0.01451  -0.0883   0.1799   1.0000
  11.750   1.5965   0.02178   0.01558  -0.0859   0.1684   1.0000
  12.000   1.6031   0.02292   0.01671  -0.0836   0.1577   1.0000
  12.250   1.6074   0.02426   0.01803  -0.0812   0.1466   1.0000
  12.500   1.6094   0.02582   0.01957  -0.0789   0.1353   1.0000
  12.750   1.6109   0.02752   0.02126  -0.0767   0.1255   1.0000
  13.000   1.6119   0.02937   0.02311  -0.0748   0.1163   1.0000
  13.250   1.6114   0.03145   0.02519  -0.0730   0.1066   1.0000
  13.500   1.6096   0.03376   0.02750  -0.0714   0.0980   1.0000
  13.750   1.6049   0.03647   0.03020  -0.0700   0.0892   1.0000
  14.000   1.6030   0.03907   0.03283  -0.0689   0.0821   1.0000
  14.250   1.5991   0.04200   0.03579  -0.0681   0.0759   1.0000
  14.500   1.5950   0.04508   0.03891  -0.0675   0.0702   1.0000
  14.750   1.5896   0.04845   0.04232  -0.0671   0.0646   1.0000
  15.000   1.5858   0.05175   0.04567  -0.0669   0.0607   1.0000
  15.250   1.5798   0.05545   0.04943  -0.0669   0.0567   1.0000
  15.500   1.5749   0.05914   0.05319  -0.0671   0.0531   1.0000
  15.750   1.5679   0.06321   0.05731  -0.0675   0.0499   1.0000
  16.000   1.5639   0.06699   0.06118  -0.0680   0.0474   1.0000
  16.250   1.5581   0.07113   0.06539  -0.0687   0.0447   1.0000
  16.500   1.5502   0.07565   0.06998  -0.0696   0.0422   1.0000
  16.750   1.5454   0.07982   0.07423  -0.0706   0.0401   1.0000
  17.000   1.5394   0.08425   0.07874  -0.0717   0.0379   1.0000
  17.250   1.5316   0.08905   0.08361  -0.0730   0.0359   1.0000
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