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EPPLER 678 AIRFOIL (e678-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 678 AIRFOIL (e678-il)
Reynolds number: 100,000
Max Cl/Cd: 45.69 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e678-il-100000-n5.txt
Download as CSV file: xf-e678-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 678 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.1963   0.10029   0.09520  -0.0941   0.9388   0.0293
  -9.000  -0.1905   0.09510   0.09002  -0.0984   0.9363   0.0284
  -8.500  -0.2182   0.08008   0.07509  -0.1067   0.9233   0.0258
  -8.250  -0.2304   0.07564   0.07069  -0.1077   0.9141   0.0255
  -8.000  -0.2408   0.06892   0.06391  -0.1138   0.9082   0.0252
  -7.750  -0.2618   0.06449   0.05941  -0.1145   0.8959   0.0249
  -7.500  -0.2750   0.05967   0.05441  -0.1155   0.8848   0.0247
  -7.250  -0.2711   0.05371   0.04807  -0.1194   0.8789   0.0244
  -7.000  -0.2740   0.04988   0.04393  -0.1186   0.8676   0.0242
  -6.750  -0.2556   0.04477   0.03823  -0.1216   0.8637   0.0242
  -6.500  -0.2483   0.04176   0.03482  -0.1205   0.8531   0.0243
  -6.250  -0.2213   0.03822   0.03066  -0.1226   0.8496   0.0250
  -6.000  -0.2020   0.03580   0.02762  -0.1224   0.8423   0.0260
  -5.750  -0.1780   0.03436   0.02609  -0.1230   0.8368   0.0272
  -5.500  -0.1466   0.03262   0.02407  -0.1244   0.8342   0.0282
  -5.250  -0.1277   0.03142   0.02263  -0.1233   0.8262   0.0289
  -5.000  -0.0997   0.03001   0.02098  -0.1237   0.8219   0.0300
  -4.750  -0.0677   0.02867   0.01939  -0.1246   0.8193   0.0314
  -4.500  -0.0492   0.02801   0.01872  -0.1236   0.8114   0.0329
  -4.250  -0.0205   0.02725   0.01788  -0.1242   0.8075   0.0364
  -4.000   0.0117   0.02632   0.01690  -0.1254   0.8052   0.0408
  -3.750   0.0341   0.02588   0.01637  -0.1250   0.7988   0.0456
  -3.500   0.0635   0.02518   0.01561  -0.1258   0.7948   0.0566
  -3.250   0.0969   0.02430   0.01487  -0.1275   0.7924   0.0842
  -3.000   0.1317   0.02333   0.01427  -0.1295   0.7907   0.1565
  -2.750   0.1554   0.02285   0.01426  -0.1301   0.7844   0.2620
  -2.500   0.1865   0.02209   0.01412  -0.1315   0.7815   0.4223
  -2.250   0.2132   0.02169   0.01417  -0.1311   0.7791   0.5525
  -2.000   0.2374   0.02162   0.01427  -0.1294   0.7772   0.6363
  -1.750   0.2548   0.02208   0.01469  -0.1273   0.7715   0.6811
  -1.500   0.2787   0.02227   0.01477  -0.1262   0.7678   0.7151
  -1.250   0.3056   0.02229   0.01466  -0.1255   0.7654   0.7408
  -1.000   0.3322   0.02224   0.01451  -0.1247   0.7636   0.7620
  -0.750   0.3519   0.02251   0.01469  -0.1229   0.7598   0.7806
  -0.500   0.3691   0.02283   0.01495  -0.1209   0.7553   0.7976
  -0.250   0.3930   0.02281   0.01484  -0.1198   0.7526   0.8125
   0.000   0.4206   0.02264   0.01457  -0.1194   0.7506   0.8250
   0.250   0.4512   0.02243   0.01425  -0.1198   0.7491   0.8365
   0.750   0.4884   0.02302   0.01474  -0.1169   0.7405   0.8570
   1.000   0.5171   0.02297   0.01461  -0.1172   0.7379   0.8662
   1.250   0.5465   0.02280   0.01437  -0.1175   0.7360   0.8744
   1.500   0.5797   0.02259   0.01409  -0.1185   0.7344   0.8821
   1.750   0.6139   0.02230   0.01374  -0.1197   0.7331   0.8894
   2.000   0.6187   0.02327   0.01474  -0.1165   0.7254   0.8986
   2.250   0.6465   0.02329   0.01473  -0.1167   0.7224   0.9067
   2.500   0.6785   0.02309   0.01450  -0.1175   0.7202   0.9143
   2.750   0.7145   0.02281   0.01420  -0.1191   0.7185   0.9223
   3.000   0.7528   0.02243   0.01379  -0.1209   0.7170   0.9300
   3.250   0.7491   0.02369   0.01514  -0.1164   0.7077   0.9445
   3.500   0.7845   0.02353   0.01500  -0.1181   0.7048   0.9560
   3.750   0.8272   0.02322   0.01468  -0.1210   0.7026   0.9700
   4.000   0.8734   0.02280   0.01428  -0.1245   0.7007   1.0000
   4.500   0.9138   0.02420   0.01577  -0.1238   0.6880   1.0000
   4.750   0.9591   0.02389   0.01549  -0.1271   0.6854   1.0000
   5.000   1.0077   0.02354   0.01515  -0.1310   0.6829   1.0000
   5.250   1.0016   0.02512   0.01683  -0.1264   0.6724   1.0000
   5.500   1.0474   0.02473   0.01650  -0.1297   0.6691   1.0000
   5.750   1.0556   0.02577   0.01762  -0.1273   0.6604   1.0000
   6.000   1.0883   0.02581   0.01773  -0.1284   0.6547   1.0000
   6.250   1.1394   0.02518   0.01716  -0.1324   0.6511   1.0000
   6.500   1.1303   0.02672   0.01882  -0.1272   0.6398   1.0000
   6.750   1.1784   0.02605   0.01821  -0.1305   0.6354   1.0000
   7.000   1.1713   0.02749   0.01979  -0.1256   0.6238   1.0000
   7.250   1.2190   0.02668   0.01904  -0.1286   0.6186   1.0000
   7.500   1.2118   0.02808   0.02057  -0.1238   0.6062   1.0000
   7.750   1.2164   0.02908   0.02168  -0.1208   0.5948   1.0000
   8.000   1.2556   0.02835   0.02105  -0.1222   0.5874   1.0000
   8.250   1.2521   0.02971   0.02253  -0.1182   0.5738   1.0000
   8.500   1.2544   0.03089   0.02383  -0.1150   0.5599   1.0000
   8.750   1.2610   0.03190   0.02495  -0.1125   0.5455   1.0000
   9.000   1.2715   0.03272   0.02587  -0.1105   0.5303   1.0000
   9.250   1.2864   0.03324   0.02649  -0.1089   0.5139   1.0000
   9.500   1.3063   0.03342   0.02672  -0.1078   0.4961   1.0000
   9.750   1.3199   0.03408   0.02742  -0.1062   0.4748   1.0000
  10.000   1.3431   0.03404   0.02733  -0.1053   0.4510   1.0000
  10.250   1.3577   0.03471   0.02795  -0.1038   0.4250   1.0000
  10.500   1.3696   0.03563   0.02878  -0.1020   0.3985   1.0000
  10.750   1.3776   0.03689   0.02995  -0.0999   0.3723   1.0000
  11.000   1.3818   0.03855   0.03155  -0.0977   0.3466   1.0000
  11.250   1.3849   0.04035   0.03330  -0.0956   0.3221   1.0000
  11.500   1.3863   0.04239   0.03527  -0.0934   0.2975   1.0000
  11.750   1.3867   0.04461   0.03742  -0.0915   0.2731   1.0000
  12.000   1.3852   0.04708   0.03979  -0.0896   0.2488   1.0000
  12.250   1.3839   0.04969   0.04233  -0.0879   0.2238   1.0000
  12.500   1.3813   0.05253   0.04506  -0.0864   0.1990   1.0000
  12.750   1.3779   0.05555   0.04796  -0.0851   0.1748   1.0000
  13.000   1.3758   0.05855   0.05087  -0.0840   0.1508   1.0000
  13.250   1.3737   0.06165   0.05389  -0.0830   0.1302   1.0000
  13.500   1.3741   0.06456   0.05679  -0.0823   0.1126   1.0000
  13.750   1.3742   0.06756   0.05979  -0.0816   0.0975   1.0000
  14.000   1.3733   0.07075   0.06298  -0.0810   0.0833   1.0000
  14.250   1.3709   0.07418   0.06640  -0.0805   0.0700   1.0000
  14.750   1.3639   0.08161   0.07384  -0.0800   0.0492   1.0000
  15.000   1.3606   0.08542   0.07772  -0.0799   0.0423   1.0000
  15.250   1.3563   0.08945   0.08183  -0.0800   0.0375   1.0000
  15.500   1.3516   0.09362   0.08611  -0.0804   0.0342   1.0000
  15.750   1.3467   0.09792   0.09051  -0.0809   0.0320   1.0000
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