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EPPLER 66 AIRFOIL (e66-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 66 AIRFOIL (e66-il)
Reynolds number: 1,000,000
Max Cl/Cd: 121.69 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e66-il-1000000-n5.txt
Download as CSV file: xf-e66-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 66 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.3803   0.12714   0.12540  -0.0407   0.9973   0.0033
 -12.000  -0.3807   0.12045   0.11872  -0.0438   0.9967   0.0036
 -11.500  -0.6689   0.03287   0.03051  -0.1144   0.9804   0.0034
 -11.250  -0.6573   0.02819   0.02551  -0.1206   0.9753   0.0034
 -11.000  -0.6347   0.02545   0.02252  -0.1243   0.9733   0.0035
 -10.750  -0.6099   0.02294   0.01975  -0.1275   0.9719   0.0035
 -10.500  -0.5965   0.02143   0.01804  -0.1266   0.9656   0.0036
 -10.250  -0.5714   0.01992   0.01634  -0.1280   0.9632   0.0036
 -10.000  -0.5440   0.01858   0.01482  -0.1295   0.9614   0.0036
  -9.750  -0.5149   0.01750   0.01359  -0.1309   0.9602   0.0037
  -9.500  -0.4892   0.01654   0.01249  -0.1315   0.9572   0.0038
  -9.250  -0.4662   0.01549   0.01129  -0.1314   0.9526   0.0038
  -9.000  -0.4378   0.01425   0.00985  -0.1326   0.9501   0.0040
  -8.750  -0.4059   0.01336   0.00883  -0.1342   0.9484   0.0042
  -8.500  -0.3732   0.01271   0.00809  -0.1358   0.9468   0.0045
  -8.250  -0.3454   0.01222   0.00754  -0.1362   0.9428   0.0048
  -8.000  -0.3157   0.01175   0.00699  -0.1369   0.9390   0.0051
  -7.750  -0.2838   0.01124   0.00639  -0.1381   0.9359   0.0054
  -7.500  -0.2508   0.01078   0.00584  -0.1396   0.9332   0.0058
  -7.250  -0.2222   0.01037   0.00535  -0.1400   0.9283   0.0059
  -7.000  -0.1922   0.00993   0.00483  -0.1407   0.9235   0.0063
  -6.750  -0.1607   0.00952   0.00435  -0.1416   0.9193   0.0071
  -6.500  -0.1325   0.00922   0.00401  -0.1419   0.9137   0.0079
  -6.250  -0.1031   0.00895   0.00368  -0.1423   0.9081   0.0088
  -6.000  -0.0738   0.00868   0.00337  -0.1428   0.9029   0.0104
  -5.750  -0.0457   0.00847   0.00314  -0.1429   0.8965   0.0126
  -5.250   0.0111   0.00808   0.00267  -0.1433   0.8840   0.0170
  -5.000   0.0395   0.00793   0.00246  -0.1435   0.8775   0.0185
  -4.750   0.0672   0.00774   0.00225  -0.1435   0.8708   0.0216
  -4.500   0.0953   0.00760   0.00207  -0.1436   0.8636   0.0249
  -4.250   0.1229   0.00740   0.00190  -0.1436   0.8564   0.0354
  -4.000   0.1505   0.00721   0.00173  -0.1436   0.8490   0.0505
  -3.750   0.1782   0.00708   0.00160  -0.1436   0.8414   0.0620
  -3.500   0.2058   0.00697   0.00148  -0.1436   0.8337   0.0741
  -3.250   0.2334   0.00685   0.00138  -0.1436   0.8256   0.0879
  -3.000   0.2609   0.00676   0.00128  -0.1435   0.8176   0.1036
  -2.750   0.2883   0.00665   0.00120  -0.1435   0.8088   0.1245
  -2.500   0.3157   0.00651   0.00114  -0.1435   0.8002   0.1557
  -2.250   0.3428   0.00642   0.00107  -0.1434   0.7911   0.1833
  -2.000   0.3702   0.00635   0.00103  -0.1433   0.7812   0.2033
  -1.750   0.3974   0.00629   0.00099  -0.1432   0.7710   0.2294
  -1.500   0.4243   0.00625   0.00097  -0.1430   0.7600   0.2542
  -1.250   0.4510   0.00622   0.00095  -0.1428   0.7481   0.2799
  -1.000   0.4780   0.00616   0.00095  -0.1427   0.7362   0.3159
  -0.750   0.5048   0.00613   0.00095  -0.1425   0.7240   0.3460
  -0.500   0.5316   0.00611   0.00096  -0.1423   0.7114   0.3770
  -0.250   0.5581   0.00610   0.00099  -0.1421   0.6982   0.4088
   0.000   0.5846   0.00611   0.00102  -0.1418   0.6839   0.4403
   0.250   0.6109   0.00613   0.00106  -0.1415   0.6691   0.4734
   0.500   0.6370   0.00616   0.00112  -0.1412   0.6531   0.5070
   0.750   0.6629   0.00621   0.00118  -0.1408   0.6363   0.5397
   1.000   0.6887   0.00628   0.00126  -0.1404   0.6189   0.5734
   1.250   0.7146   0.00634   0.00134  -0.1400   0.6006   0.6064
   1.500   0.7402   0.00643   0.00143  -0.1396   0.5811   0.6384
   2.000   0.7907   0.00664   0.00166  -0.1386   0.5400   0.7064
   2.250   0.8153   0.00678   0.00179  -0.1379   0.5167   0.7392
   2.500   0.8398   0.00694   0.00193  -0.1373   0.4919   0.7723
   2.750   0.8637   0.00711   0.00209  -0.1365   0.4666   0.8039
   3.000   0.8870   0.00729   0.00226  -0.1356   0.4415   0.8370
   3.250   0.9092   0.00749   0.00243  -0.1344   0.4154   0.8719
   3.500   0.9293   0.00766   0.00259  -0.1327   0.3896   0.9110
   3.750   0.9504   0.00781   0.00272  -0.1312   0.3637   1.0000
   4.000   0.9744   0.00812   0.00291  -0.1306   0.3367   1.0000
   4.250   0.9975   0.00851   0.00314  -0.1298   0.3041   1.0000
   4.500   1.0199   0.00893   0.00339  -0.1289   0.2688   1.0000
   4.750   1.0432   0.00930   0.00364  -0.1281   0.2429   1.0000
   5.000   1.0670   0.00961   0.00387  -0.1275   0.2225   1.0000
   5.250   1.0894   0.01002   0.00415  -0.1266   0.1959   1.0000
   5.500   1.1099   0.01057   0.00450  -0.1254   0.1594   1.0000
   5.750   1.1316   0.01102   0.00483  -0.1244   0.1347   1.0000
   6.000   1.1536   0.01144   0.00515  -0.1234   0.1143   1.0000
   6.500   1.1966   0.01230   0.00584  -0.1213   0.0801   1.0000
   6.750   1.2182   0.01271   0.00619  -0.1203   0.0678   1.0000
   7.000   1.2395   0.01312   0.00656  -0.1192   0.0570   1.0000
   7.250   1.2603   0.01355   0.00695  -0.1180   0.0471   1.0000
   7.500   1.2803   0.01397   0.00733  -0.1167   0.0388   1.0000
   7.750   1.2995   0.01440   0.00774  -0.1152   0.0316   1.0000
   8.000   1.3173   0.01490   0.00820  -0.1135   0.0236   1.0000
   8.250   1.3347   0.01542   0.00868  -0.1117   0.0178   1.0000
   8.500   1.3521   0.01592   0.00918  -0.1100   0.0144   1.0000
   8.750   1.3707   0.01636   0.00965  -0.1084   0.0129   1.0000
   9.000   1.3883   0.01683   0.01014  -0.1068   0.0115   1.0000
   9.250   1.4051   0.01737   0.01070  -0.1050   0.0102   1.0000
   9.500   1.4225   0.01787   0.01124  -0.1034   0.0095   1.0000
   9.750   1.4398   0.01835   0.01177  -0.1018   0.0089   1.0000
  10.000   1.4564   0.01889   0.01235  -0.1001   0.0084   1.0000
  10.250   1.4721   0.01949   0.01299  -0.0983   0.0076   1.0000
  10.500   1.4866   0.02016   0.01370  -0.0964   0.0069   1.0000
  10.750   1.5017   0.02081   0.01440  -0.0946   0.0064   1.0000
  11.000   1.5168   0.02144   0.01508  -0.0928   0.0058   1.0000
  11.250   1.5307   0.02216   0.01584  -0.0910   0.0052   1.0000
  11.500   1.5434   0.02298   0.01669  -0.0891   0.0045   1.0000
  11.750   1.5559   0.02382   0.01759  -0.0871   0.0041   1.0000
  12.000   1.5680   0.02470   0.01853  -0.0853   0.0037   1.0000
  12.250   1.5794   0.02565   0.01955  -0.0834   0.0034   1.0000
  12.500   1.5895   0.02672   0.02067  -0.0814   0.0030   1.0000
  12.750   1.5981   0.02793   0.02195  -0.0794   0.0027   1.0000
  13.000   1.6075   0.02910   0.02320  -0.0775   0.0026   1.0000
  13.250   1.6162   0.03037   0.02454  -0.0757   0.0025   1.0000
  13.500   1.6240   0.03173   0.02600  -0.0739   0.0024   1.0000
  13.750   1.6312   0.03319   0.02754  -0.0722   0.0023   1.0000
  14.000   1.6371   0.03480   0.02924  -0.0706   0.0022   1.0000
  14.250   1.6424   0.03652   0.03105  -0.0690   0.0021   1.0000
  14.500   1.6467   0.03841   0.03303  -0.0675   0.0020   1.0000
  14.750   1.6498   0.04046   0.03517  -0.0661   0.0019   1.0000
  15.000   1.6525   0.04263   0.03745  -0.0649   0.0019   1.0000
  15.250   1.6536   0.04506   0.03999  -0.0639   0.0018   1.0000
  15.500   1.6530   0.04781   0.04285  -0.0629   0.0017   1.0000
  15.750   1.6507   0.05085   0.04601  -0.0623   0.0016   1.0000
  16.000   1.6473   0.05419   0.04947  -0.0618   0.0016   1.0000
  16.250   1.6409   0.05807   0.05350  -0.0617   0.0015   1.0000
  16.500   1.6353   0.06203   0.05758  -0.0619   0.0015   1.0000
  16.750   1.6299   0.06614   0.06182  -0.0625   0.0015   1.0000
  17.000   1.6243   0.07046   0.06627  -0.0633   0.0015   1.0000
  17.250   1.6165   0.07532   0.07126  -0.0645   0.0014   1.0000
  17.500   1.6074   0.08056   0.07665  -0.0662   0.0014   1.0000
  17.750   1.5970   0.08626   0.08248  -0.0682   0.0014   1.0000
  18.000   1.5851   0.09242   0.08878  -0.0707   0.0014   1.0000
  18.250   1.5712   0.09919   0.09570  -0.0737   0.0014   1.0000
  18.500   1.5560   0.10640   0.10307  -0.0771   0.0014   1.0000
  18.750   1.5389   0.11422   0.11104  -0.0811   0.0014   1.0000
  19.000   1.5211   0.12243   0.11940  -0.0856   0.0014   1.0000
  19.250   1.5012   0.13125   0.12837  -0.0906   0.0014   1.0000
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