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EPPLER 49 AIRFOIL (e49-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 49 AIRFOIL (e49-il)
Reynolds number: 100,000
Max Cl/Cd: 50.94 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e49-il-100000-n5.txt
Download as CSV file: xf-e49-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 49 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
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3096   0.11328   0.10873  -0.0332   0.9675   0.0223
  -7.250  -0.3019   0.11078   0.10624  -0.0353   0.9642   0.0228
  -7.000  -0.3035   0.10845   0.10395  -0.0347   0.9584   0.0232
  -6.750  -0.2963   0.10558   0.10110  -0.0366   0.9541   0.0239
  -6.500  -0.2823   0.10232   0.09773  -0.0404   0.9509   0.0246
  -6.250  -0.2757   0.09930   0.09473  -0.0421   0.9452   0.0253
  -6.000  -0.2606   0.09584   0.09127  -0.0464   0.9406   0.0260
  -5.750  -0.2347   0.09175   0.08716  -0.0538   0.9374   0.0264
  -5.500  -0.2173   0.08802   0.08341  -0.0584   0.9316   0.0265
  -5.250  -0.1864   0.08352   0.07885  -0.0665   0.9274   0.0267
  -5.000  -0.1727   0.08017   0.07553  -0.0665   0.9248   0.0277
  -4.750  -0.1464   0.07643   0.07175  -0.0715   0.9212   0.0298
  -4.500  -0.1108   0.07181   0.06706  -0.0797   0.9164   0.0319
  -4.250  -0.0749   0.06781   0.06296  -0.0863   0.9134   0.0351
  -3.750   0.0246   0.05917   0.05399  -0.1061   0.9100   0.0583
  -3.250   0.1019   0.05269   0.04717  -0.1170   0.9034   0.0777
  -2.750   0.2177   0.04346   0.03678  -0.1321   0.9009   0.0391
  -2.500   0.2597   0.04090   0.03383  -0.1359   0.8989   0.0332
  -2.250   0.3025   0.03879   0.03121  -0.1393   0.8972   0.0304
  -2.000   0.3436   0.03714   0.02887  -0.1421   0.8957   0.0281
  -1.750   0.3836   0.03581   0.02706  -0.1445   0.8943   0.0280
  -1.500   0.4067   0.03491   0.02589  -0.1439   0.8878   0.0285
  -1.250   0.4380   0.03435   0.02503  -0.1449   0.8838   0.0373
  -1.000   0.4719   0.03362   0.02417  -0.1463   0.8812   0.0408
  -0.750   0.5071   0.03298   0.02340  -0.1476   0.8792   0.0403
  -0.500   0.5281   0.03261   0.02299  -0.1466   0.8720   0.0402
  -0.250   0.5580   0.03228   0.02257  -0.1472   0.8675   0.0403
   0.000   0.5924   0.03201   0.02219  -0.1487   0.8645   0.0411
   0.250   0.6288   0.03179   0.02182  -0.1504   0.8623   0.0426
   0.500   0.6459   0.03177   0.02177  -0.1487   0.8523   0.0461
   0.750   0.6828   0.03116   0.02179  -0.1510   0.8493   0.2841
   1.250   0.7306   0.02988   0.02157  -0.1498   0.8359   1.0000
   1.500   0.7650   0.02970   0.02127  -0.1511   0.8320   1.0000
   1.750   0.7853   0.02978   0.02130  -0.1499   0.8216   1.0000
   2.000   0.8201   0.02943   0.02090  -0.1511   0.8168   1.0000
   2.250   0.8417   0.02943   0.02089  -0.1501   0.8057   1.0000
   2.500   0.8771   0.02895   0.02040  -0.1513   0.8009   1.0000
   2.750   0.8979   0.02901   0.02049  -0.1502   0.7893   1.0000
   3.000   0.9328   0.02849   0.02009  -0.1512   0.7848   1.0000
   3.250   0.9534   0.02858   0.02023  -0.1500   0.7729   1.0000
   3.500   0.9812   0.02832   0.02002  -0.1499   0.7646   1.0000
   3.750   1.0096   0.02797   0.01976  -0.1498   0.7555   1.0000
   4.000   1.0354   0.02777   0.01964  -0.1493   0.7437   1.0000
   4.250   1.0671   0.02718   0.01913  -0.1496   0.7324   1.0000
   4.500   1.1022   0.02637   0.01855  -0.1503   0.7188   1.0000
   4.750   1.1379   0.02564   0.01794  -0.1512   0.7029   1.0000
   5.000   1.1987   0.02353   0.01386  -0.1538   0.4216   1.0000
   5.250   1.2010   0.02550   0.01490  -0.1499   0.2910   1.0000
   5.500   1.2038   0.02782   0.01620  -0.1465   0.1503   1.0000
   5.750   1.2057   0.03057   0.01795  -0.1431   0.0128   1.0000
   6.000   1.2222   0.03155   0.01903  -0.1414   0.0103   1.0000
   6.250   1.2383   0.03258   0.02024  -0.1396   0.0091   1.0000
   6.500   1.2537   0.03368   0.02155  -0.1378   0.0085   1.0000
   6.750   1.2667   0.03511   0.02335  -0.1356   0.0078   1.0000
   7.000   1.2793   0.03653   0.02498  -0.1334   0.0076   1.0000
   7.250   1.2907   0.03803   0.02671  -0.1312   0.0076   1.0000
   7.500   1.3002   0.03966   0.02857  -0.1288   0.0075   1.0000
   7.750   1.3074   0.04149   0.03063  -0.1261   0.0075   1.0000
   8.000   1.3133   0.04348   0.03282  -0.1234   0.0075   1.0000
   8.250   1.3187   0.04558   0.03511  -0.1207   0.0075   1.0000
   8.500   1.3249   0.04781   0.03751  -0.1183   0.0076   1.0000
   8.750   1.3336   0.05012   0.03998  -0.1162   0.0076   1.0000
   9.000   1.3464   0.05253   0.04254  -0.1147   0.0076   1.0000
   9.250   1.3644   0.05509   0.04526  -0.1137   0.0077   1.0000
   9.750   1.3979   0.06007   0.05076  -0.1117   0.0078   1.0000
  10.000   1.4100   0.06274   0.05371  -0.1103   0.0079   1.0000
  10.250   1.4182   0.06558   0.05685  -0.1085   0.0080   1.0000
  10.500   1.4225   0.06860   0.06020  -0.1064   0.0082   1.0000
  10.750   1.4232   0.07188   0.06382  -0.1043   0.0083   1.0000
  11.000   1.4205   0.07545   0.06774  -0.1020   0.0084   1.0000
  11.250   1.4146   0.07930   0.07195  -0.0999   0.0085   1.0000
  11.500   1.4056   0.08348   0.07648  -0.0980   0.0087   1.0000
  11.750   1.3941   0.08796   0.08129  -0.0965   0.0088   1.0000
  12.000   1.3806   0.09275   0.08640  -0.0956   0.0089   1.0000
  12.250   1.3658   0.09788   0.09183  -0.0953   0.0090   1.0000
  12.500   1.3495   0.10340   0.09765  -0.0957   0.0091   1.0000
  12.750   1.3321   0.10939   0.10391  -0.0971   0.0092   1.0000
  13.000   1.3147   0.11580   0.11058  -0.0993   0.0093   1.0000
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