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EPPLER 604 AIRFOIL (e604-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 604 AIRFOIL (e604-il)
Reynolds number: 100,000
Max Cl/Cd: 30.12 at α=10.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e604-il-100000-n5.txt
Download as CSV file: xf-e604-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 604 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
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.3204   0.10908   0.10420  -0.0800   0.9825   0.0226
 -12.750  -0.4431   0.07538   0.07000  -0.1009   0.9740   0.0204
 -12.500  -0.4601   0.06868   0.06308  -0.1062   0.9651   0.0203
 -12.250  -0.4733   0.06275   0.05686  -0.1109   0.9574   0.0203
 -12.000  -0.4861   0.05774   0.05153  -0.1138   0.9473   0.0203
 -11.750  -0.4898   0.05341   0.04686  -0.1166   0.9398   0.0204
 -11.500  -0.4854   0.05011   0.04334  -0.1186   0.9319   0.0206
 -11.250  -0.4755   0.04722   0.04024  -0.1206   0.9254   0.0210
 -11.000  -0.4674   0.04464   0.03740  -0.1215   0.9167   0.0214
 -10.750  -0.4517   0.04202   0.03451  -0.1231   0.9114   0.0221
 -10.500  -0.4411   0.03999   0.03222  -0.1228   0.9020   0.0227
 -10.250  -0.4208   0.03775   0.02960  -0.1238   0.8965   0.0240
 -10.000  -0.4064   0.03631   0.02802  -0.1234   0.8880   0.0254
  -9.750  -0.3854   0.03492   0.02649  -0.1240   0.8817   0.0271
  -9.500  -0.3601   0.03341   0.02471  -0.1242   0.8764   0.0289
  -9.250  -0.3405   0.03222   0.02348  -0.1237   0.8694   0.0304
  -9.000  -0.3174   0.03110   0.02225  -0.1240   0.8642   0.0331
  -8.750  -0.3003   0.03020   0.02126  -0.1231   0.8575   0.0362
  -8.500  -0.2831   0.02935   0.02035  -0.1222   0.8509   0.0397
  -8.250  -0.2620   0.02835   0.01929  -0.1221   0.8462   0.0440
  -8.000  -0.2515   0.02778   0.01863  -0.1199   0.8386   0.0490
  -7.750  -0.2381   0.02700   0.01788  -0.1185   0.8329   0.0548
  -7.500  -0.2223   0.02624   0.01707  -0.1174   0.8285   0.0617
  -7.250  -0.2181   0.02586   0.01668  -0.1141   0.8210   0.0691
  -7.000  -0.2053   0.02522   0.01602  -0.1124   0.8158   0.0797
  -6.750  -0.1915   0.02455   0.01538  -0.1109   0.8113   0.0941
  -6.500  -0.1868   0.02415   0.01507  -0.1078   0.8045   0.1092
  -6.250  -0.1748   0.02354   0.01456  -0.1059   0.8000   0.1343
  -6.000  -0.1605   0.02273   0.01395  -0.1046   0.7965   0.1763
  -5.750  -0.1612   0.02223   0.01372  -0.1008   0.7895   0.2225
  -5.500  -0.1567   0.02124   0.01316  -0.0983   0.7844   0.3066
  -5.250  -0.1454   0.02065   0.01346  -0.0954   0.7811   0.4539
  -5.000  -0.1239   0.02151   0.01454  -0.0928   0.7773   0.5440
  -4.750  -0.1091   0.02187   0.01479  -0.0907   0.7719   0.5781
  -4.500  -0.0843   0.02232   0.01507  -0.0897   0.7681   0.6024
  -4.250  -0.0565   0.02268   0.01524  -0.0894   0.7653   0.6221
  -4.000  -0.0273   0.02327   0.01569  -0.0887   0.7629   0.6360
  -3.750  -0.0171   0.02399   0.01637  -0.0852   0.7569   0.6473
  -3.500   0.0047   0.02458   0.01686  -0.0834   0.7530   0.6611
  -3.250   0.0308   0.02499   0.01713  -0.0826   0.7500   0.6751
  -3.000   0.0615   0.02554   0.01757  -0.0817   0.7479   0.6813
  -2.750   0.0715   0.02562   0.01757  -0.0795   0.7426   0.6915
  -2.500   0.0887   0.02597   0.01787  -0.0772   0.7380   0.6952
  -2.250   0.1140   0.02602   0.01782  -0.0767   0.7349   0.6999
  -2.000   0.1432   0.02571   0.01734  -0.0779   0.7324   0.7067
  -1.750   0.1747   0.02556   0.01707  -0.0787   0.7306   0.7100
  -1.500   0.1727   0.02606   0.01761  -0.0738   0.7231   0.7134
  -1.250   0.1961   0.02602   0.01748  -0.0735   0.7195   0.7168
  -1.000   0.2263   0.02580   0.01715  -0.0746   0.7170   0.7208
  -0.750   0.2608   0.02547   0.01668  -0.0768   0.7151   0.7250
  -0.500   0.2617   0.02596   0.01721  -0.0726   0.7082   0.7274
  -0.250   0.2816   0.02606   0.01728  -0.0716   0.7040   0.7300
   0.000   0.3107   0.02597   0.01711  -0.0722   0.7014   0.7325
   0.250   0.3447   0.02576   0.01682  -0.0737   0.6994   0.7351
   0.750   0.3712   0.02633   0.01736  -0.0708   0.6883   0.7424
   1.000   0.3998   0.02627   0.01726  -0.0711   0.6855   0.7441
   1.250   0.4333   0.02611   0.01705  -0.0724   0.6835   0.7460
   1.500   0.4659   0.02599   0.01690  -0.0735   0.6813   0.7482
   1.750   0.4526   0.02697   0.01795  -0.0677   0.6715   0.7522
   2.000   0.4868   0.02684   0.01778  -0.0694   0.6690   0.7552
   2.250   0.5264   0.02661   0.01750  -0.0720   0.6672   0.7578
   2.500   0.5622   0.02642   0.01729  -0.0735   0.6655   0.7594
   2.750   0.5372   0.02769   0.01868  -0.0658   0.6542   0.7624
   3.000   0.5716   0.02751   0.01850  -0.0670   0.6521   0.7648
   3.250   0.6107   0.02724   0.01822  -0.0691   0.6504   0.7674
   4.000   0.6654   0.02816   0.01924  -0.0665   0.6349   0.7761
   4.250   0.7049   0.02777   0.01887  -0.0684   0.6333   0.7780
   4.750   0.7191   0.02919   0.02042  -0.0634   0.6190   0.7846
   5.000   0.7587   0.02873   0.01999  -0.0653   0.6170   0.7877
   5.500   0.7811   0.02997   0.02136  -0.0617   0.6028   0.7938
   6.000   0.8037   0.03132   0.02287  -0.0584   0.5881   0.8002
   6.250   0.8304   0.03131   0.02291  -0.0586   0.5834   0.8036
   6.750   0.8720   0.03165   0.02342  -0.0574   0.5711   0.8105
   7.250   0.9018   0.03268   0.02461  -0.0551   0.5559   0.8181
   7.750   0.9363   0.03349   0.02560  -0.0535   0.5405   0.8255
   8.250   0.9718   0.03412   0.02642  -0.0517   0.5247   0.8338
   8.750   1.0127   0.03439   0.02687  -0.0504   0.5082   0.8430
   9.000   1.0135   0.03591   0.02849  -0.0483   0.4956   0.8481
   9.250   1.0305   0.03639   0.02907  -0.0476   0.4856   0.8534
   9.500   1.0596   0.03580   0.02857  -0.0474   0.4773   0.8581
   9.750   1.0671   0.03688   0.02974  -0.0459   0.4645   0.8638
  10.250   1.1040   0.03733   0.03035  -0.0442   0.4406   0.8769
  10.500   1.1251   0.03736   0.03043  -0.0435   0.4276   0.8849
  10.750   1.1383   0.03787   0.03101  -0.0421   0.4131   0.8935
  11.000   1.1491   0.03868   0.03188  -0.0408   0.3977   0.9038
  11.250   1.1597   0.03947   0.03272  -0.0395   0.3818   0.9172
  11.500   1.1695   0.04030   0.03359  -0.0382   0.3655   0.9407
  11.750   1.1765   0.04146   0.03477  -0.0373   0.3484   1.0000
  12.000   1.1868   0.04300   0.03630  -0.0370   0.3307   1.0000
  12.250   1.1958   0.04464   0.03793  -0.0366   0.3130   1.0000
  12.500   1.2038   0.04641   0.03966  -0.0363   0.2957   1.0000
  12.750   1.2105   0.04829   0.04151  -0.0359   0.2790   1.0000
  13.000   1.2163   0.05032   0.04351  -0.0355   0.2630   1.0000
  13.250   1.2210   0.05249   0.04566  -0.0351   0.2474   1.0000
  13.500   1.2250   0.05477   0.04792  -0.0348   0.2326   1.0000
  13.750   1.2284   0.05716   0.05032  -0.0345   0.2185   1.0000
  14.000   1.2312   0.05966   0.05280  -0.0343   0.2051   1.0000
  14.250   1.2336   0.06227   0.05540  -0.0342   0.1925   1.0000
  14.500   1.2353   0.06500   0.05812  -0.0341   0.1805   1.0000
  14.750   1.2374   0.06778   0.06095  -0.0342   0.1689   1.0000
  15.000   1.2389   0.07067   0.06388  -0.0343   0.1582   1.0000
  15.250   1.2397   0.07369   0.06689  -0.0345   0.1484   1.0000
  15.500   1.2403   0.07680   0.07006  -0.0349   0.1388   1.0000
  15.750   1.2414   0.07992   0.07324  -0.0353   0.1299   1.0000
  16.000   1.2405   0.08328   0.07659  -0.0358   0.1222   1.0000
  16.250   1.2415   0.08654   0.07997  -0.0364   0.1142   1.0000
  16.500   1.2408   0.09003   0.08347  -0.0371   0.1074   1.0000
  16.750   1.2405   0.09354   0.08709  -0.0380   0.1005   1.0000
  17.000   1.2394   0.09716   0.09073  -0.0389   0.0947   1.0000
  17.250   1.2388   0.10082   0.09451  -0.0400   0.0887   1.0000
  17.500   1.2368   0.10464   0.09832  -0.0411   0.0839   1.0000
  17.750   1.2366   0.10834   0.10219  -0.0424   0.0784   1.0000
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