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EPPLER 67 AIRFOIL (e67-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 67 AIRFOIL (e67-il)
Reynolds number: 100,000
Max Cl/Cd: 60.29 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e67-il-100000-n5.txt
Download as CSV file: xf-e67-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 67 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4170   0.09458   0.08980  -0.0449   1.0000   0.0255
  -9.250  -0.4322   0.09021   0.08552  -0.0449   1.0000   0.0251
  -9.000  -0.4538   0.08505   0.08047  -0.0451   1.0000   0.0247
  -8.750  -0.5181   0.07112   0.06663  -0.0498   1.0000   0.0232
  -8.500  -0.5343   0.06164   0.05703  -0.0618   0.9927   0.0230
  -8.250  -0.5346   0.05276   0.04770  -0.0727   0.9837   0.0228
  -8.000  -0.5301   0.04646   0.04085  -0.0777   0.9755   0.0229
  -7.750  -0.5135   0.04108   0.03479  -0.0819   0.9704   0.0231
  -7.500  -0.4971   0.03736   0.03064  -0.0833   0.9644   0.0236
  -7.250  -0.4714   0.03493   0.02795  -0.0854   0.9605   0.0247
  -7.000  -0.4449   0.03313   0.02587  -0.0869   0.9565   0.0263
  -6.750  -0.4209   0.03127   0.02366  -0.0875   0.9513   0.0284
  -6.500  -0.3912   0.02918   0.02109  -0.0888   0.9478   0.0302
  -6.250  -0.3596   0.02721   0.01886  -0.0903   0.9453   0.0320
  -6.000  -0.3373   0.02603   0.01759  -0.0900   0.9394   0.0339
  -5.750  -0.3074   0.02485   0.01625  -0.0909   0.9354   0.0379
  -5.500  -0.2744   0.02380   0.01509  -0.0926   0.9325   0.0448
  -5.250  -0.2482   0.02292   0.01406  -0.0927   0.9273   0.0531
  -5.000  -0.2192   0.02214   0.01327  -0.0935   0.9226   0.0667
  -4.750  -0.1858   0.02144   0.01255  -0.0951   0.9194   0.0855
  -4.500  -0.1549   0.02082   0.01193  -0.0961   0.9154   0.1067
  -4.250  -0.1287   0.02034   0.01145  -0.0962   0.9094   0.1301
  -4.000  -0.0953   0.01981   0.01095  -0.0976   0.9059   0.1593
  -3.750  -0.0593   0.01930   0.01052  -0.0995   0.9034   0.1958
  -3.500  -0.0371   0.01902   0.01031  -0.0988   0.8959   0.2297
  -3.250  -0.0040   0.01862   0.00999  -0.1000   0.8921   0.2746
  -3.000   0.0319   0.01821   0.00969  -0.1018   0.8895   0.3253
  -2.750   0.0546   0.01803   0.00962  -0.1010   0.8820   0.3692
  -2.500   0.0872   0.01773   0.00943  -0.1020   0.8780   0.4217
  -2.250   0.1229   0.01741   0.00920  -0.1034   0.8754   0.4750
  -2.000   0.1447   0.01734   0.00923  -0.1022   0.8675   0.5187
  -1.750   0.1770   0.01712   0.00910  -0.1028   0.8635   0.5668
  -1.500   0.2126   0.01687   0.00891  -0.1040   0.8607   0.6139
  -1.250   0.2325   0.01688   0.00899  -0.1023   0.8521   0.6521
  -1.000   0.2653   0.01669   0.00885  -0.1028   0.8482   0.6941
  -0.750   0.2895   0.01663   0.00884  -0.1017   0.8416   0.7316
  -0.500   0.3162   0.01651   0.00876  -0.1009   0.8356   0.7698
  -0.250   0.3477   0.01627   0.00856  -0.1009   0.8321   0.8081
   0.000   0.3644   0.01628   0.00862  -0.0983   0.8228   0.8460
   0.250   0.3957   0.01603   0.00838  -0.0983   0.8186   0.8886
   0.500   0.4253   0.01597   0.00834  -0.0984   0.8107   0.9410
   0.750   0.4697   0.01575   0.00807  -0.1018   0.8057   1.0000
   1.000   0.4986   0.01579   0.00803  -0.1022   0.7980   1.0000
   1.250   0.5318   0.01573   0.00790  -0.1032   0.7915   1.0000
   1.500   0.5604   0.01577   0.00790  -0.1035   0.7833   1.0000
   1.750   0.5941   0.01570   0.00778  -0.1045   0.7764   1.0000
   2.000   0.6209   0.01578   0.00783  -0.1044   0.7671   1.0000
   2.250   0.6570   0.01566   0.00769  -0.1058   0.7605   1.0000
   2.500   0.6818   0.01578   0.00781  -0.1052   0.7497   1.0000
   2.750   0.7108   0.01582   0.00784  -0.1054   0.7401   1.0000
   3.000   0.7446   0.01575   0.00775  -0.1063   0.7315   1.0000
   3.250   0.7699   0.01586   0.00790  -0.1058   0.7198   1.0000
   3.500   0.7970   0.01594   0.00800  -0.1055   0.7080   1.0000
   3.750   0.8250   0.01600   0.00807  -0.1054   0.6958   1.0000
   4.000   0.8531   0.01606   0.00815  -0.1053   0.6830   1.0000
   4.250   0.8805   0.01615   0.00827  -0.1050   0.6692   1.0000
   4.500   0.9070   0.01626   0.00841  -0.1046   0.6543   1.0000
   4.750   0.9327   0.01639   0.00856  -0.1040   0.6383   1.0000
   5.000   0.9580   0.01654   0.00873  -0.1034   0.6212   1.0000
   5.250   0.9834   0.01670   0.00892  -0.1027   0.6031   1.0000
   5.500   1.0067   0.01692   0.00916  -0.1017   0.5834   1.0000
   5.750   1.0291   0.01717   0.00941  -0.1006   0.5620   1.0000
   6.000   1.0510   0.01745   0.00969  -0.0993   0.5393   1.0000
   6.250   1.0719   0.01778   0.01002  -0.0979   0.5149   1.0000
   6.500   1.0909   0.01817   0.01039  -0.0963   0.4883   1.0000
   6.750   1.1088   0.01862   0.01079  -0.0944   0.4601   1.0000
   7.000   1.1251   0.01914   0.01124  -0.0923   0.4300   1.0000
   7.250   1.1396   0.01974   0.01175  -0.0900   0.3988   1.0000
   7.500   1.1519   0.02039   0.01235  -0.0874   0.3666   1.0000
   7.750   1.1626   0.02114   0.01300  -0.0846   0.3342   1.0000
   8.000   1.1723   0.02199   0.01373  -0.0818   0.3020   1.0000
   8.250   1.1813   0.02293   0.01456  -0.0790   0.2708   1.0000
   8.500   1.1897   0.02395   0.01547  -0.0762   0.2411   1.0000
   8.750   1.1980   0.02504   0.01647  -0.0736   0.2132   1.0000
   9.000   1.2059   0.02621   0.01755  -0.0711   0.1865   1.0000
   9.250   1.2135   0.02745   0.01875  -0.0686   0.1618   1.0000
   9.500   1.2202   0.02879   0.02001  -0.0662   0.1396   1.0000
   9.750   1.2268   0.03021   0.02136  -0.0639   0.1186   1.0000
  10.000   1.2327   0.03173   0.02282  -0.0617   0.1012   1.0000
  10.250   1.2390   0.03328   0.02436  -0.0597   0.0856   1.0000
  10.500   1.2443   0.03495   0.02603  -0.0576   0.0728   1.0000
  10.750   1.2481   0.03679   0.02787  -0.0556   0.0629   1.0000
  11.000   1.2519   0.03870   0.02983  -0.0538   0.0547   1.0000
  11.250   1.2549   0.04076   0.03199  -0.0519   0.0488   1.0000
  11.500   1.2564   0.04299   0.03432  -0.0502   0.0441   1.0000
  11.750   1.2576   0.04535   0.03678  -0.0486   0.0400   1.0000
  12.000   1.2603   0.04763   0.03919  -0.0473   0.0362   1.0000
  12.250   1.2594   0.05032   0.04195  -0.0462   0.0337   1.0000
  12.500   1.2594   0.05309   0.04485  -0.0450   0.0318   1.0000
  12.750   1.2616   0.05574   0.04770  -0.0440   0.0300   1.0000
  13.000   1.2633   0.05850   0.05062  -0.0432   0.0283   1.0000
  13.250   1.2637   0.06142   0.05365  -0.0428   0.0267   1.0000
  13.500   1.2619   0.06466   0.05698  -0.0425   0.0254   1.0000
  13.750   1.2612   0.06800   0.06045  -0.0423   0.0241   1.0000
  14.000   1.2622   0.07127   0.06397  -0.0421   0.0231   1.0000
  14.250   1.2621   0.07479   0.06772  -0.0421   0.0222   1.0000
  14.500   1.2605   0.07859   0.07173  -0.0423   0.0215   1.0000
  14.750   1.2574   0.08267   0.07602  -0.0429   0.0208   1.0000
  15.000   1.2529   0.08702   0.08060  -0.0438   0.0203   1.0000
  15.250   1.2472   0.09161   0.08536  -0.0452   0.0198   1.0000
  15.500   1.2407   0.09645   0.09037  -0.0469   0.0193   1.0000
  15.750   1.2334   0.10153   0.09559  -0.0489   0.0188   1.0000
  16.000   1.2254   0.10689   0.10108  -0.0512   0.0184   1.0000
  16.500   1.2027   0.11963   0.11421  -0.0576   0.0179   1.0000
  16.750   1.1881   0.12720   0.12202  -0.0621   0.0178   1.0000
  17.000   1.1730   0.13523   0.13027  -0.0670   0.0178   1.0000
  17.250   1.1568   0.14398   0.13921  -0.0727   0.0178   1.0000
  17.500   1.1398   0.15340   0.14880  -0.0790   0.0179   1.0000
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