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EPPLER 817 HYDROFOIL AIRFOIL (e817-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 817 HYDROFOIL AIRFOIL (e817-il)
Reynolds number: 1,000,000
Max Cl/Cd: 138.07 at α=2.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e817-il-1000000.txt
Download as CSV file: xf-e817-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 817 HYDROFOIL 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.750  -0.3506   0.14679   0.14522  -0.0440   0.9978   0.0061
 -14.500  -0.3458   0.14366   0.14208  -0.0460   0.9972   0.0063
  -8.250  -0.4210   0.01819   0.01390  -0.1291   0.9343   0.0041
  -8.000  -0.4036   0.01555   0.01096  -0.1283   0.9300   0.0036
  -7.750  -0.3865   0.01383   0.00903  -0.1271   0.9254   0.0032
  -7.500  -0.3656   0.01256   0.00755  -0.1266   0.9217   0.0031
  -7.250  -0.3411   0.01168   0.00651  -0.1266   0.9188   0.0030
  -7.000  -0.3152   0.01095   0.00561  -0.1268   0.9163   0.0030
  -6.750  -0.2896   0.01041   0.00497  -0.1268   0.9137   0.0031
  -6.500  -0.2630   0.00994   0.00439  -0.1269   0.9111   0.0033
  -6.250  -0.2357   0.00958   0.00394  -0.1271   0.9088   0.0037
  -6.000  -0.2080   0.00916   0.00343  -0.1273   0.9068   0.0084
  -5.750  -0.1810   0.00849   0.00297  -0.1278   0.9049   0.0542
  -5.500  -0.1538   0.00786   0.00260  -0.1284   0.9030   0.1183
  -5.250  -0.1272   0.00723   0.00229  -0.1290   0.9012   0.1990
  -5.000  -0.0995   0.00689   0.00214  -0.1294   0.8994   0.2512
  -4.750  -0.0714   0.00666   0.00204  -0.1298   0.8975   0.2906
  -4.500  -0.0428   0.00654   0.00195  -0.1302   0.8957   0.3116
  -4.250  -0.0140   0.00646   0.00185  -0.1306   0.8941   0.3232
  -4.000   0.0149   0.00637   0.00179  -0.1310   0.8927   0.3398
  -3.750   0.0439   0.00631   0.00174  -0.1315   0.8913   0.3569
  -3.500   0.0728   0.00626   0.00171  -0.1319   0.8899   0.3716
  -3.250   0.1011   0.00621   0.00168  -0.1321   0.8884   0.3825
  -3.000   0.1296   0.00615   0.00163  -0.1324   0.8867   0.3931
  -2.750   0.1582   0.00611   0.00161  -0.1328   0.8851   0.4035
  -2.500   0.1870   0.00607   0.00159  -0.1331   0.8836   0.4140
  -2.250   0.2159   0.00603   0.00157  -0.1335   0.8820   0.4250
  -2.000   0.2449   0.00599   0.00156  -0.1338   0.8805   0.4359
  -1.750   0.2740   0.00597   0.00155  -0.1342   0.8790   0.4465
  -1.500   0.3031   0.00598   0.00157  -0.1346   0.8772   0.4578
  -1.250   0.3312   0.00594   0.00159  -0.1348   0.8752   0.4692
  -1.000   0.3594   0.00591   0.00160  -0.1350   0.8728   0.4802
  -0.750   0.3879   0.00587   0.00160  -0.1352   0.8703   0.4910
  -0.500   0.4168   0.00583   0.00159  -0.1355   0.8674   0.5025
  -0.250   0.4459   0.00581   0.00159  -0.1358   0.8643   0.5141
   0.000   0.4734   0.00577   0.00161  -0.1357   0.8604   0.5253
   0.250   0.5015   0.00572   0.00161  -0.1358   0.8560   0.5370
   0.500   0.5303   0.00567   0.00160  -0.1360   0.8519   0.5490
   0.750   0.5577   0.00563   0.00161  -0.1359   0.8464   0.5605
   1.000   0.5856   0.00557   0.00159  -0.1358   0.8404   0.5718
   1.250   0.6131   0.00553   0.00161  -0.1357   0.8336   0.5837
   1.500   0.6403   0.00547   0.00158  -0.1355   0.8236   0.5957
   1.750   0.6666   0.00542   0.00157  -0.1350   0.8123   0.6077
   2.000   0.6928   0.00539   0.00158  -0.1346   0.7979   0.6199
   2.500   0.7456   0.00540   0.00169  -0.1339   0.7672   0.6448
   2.750   0.7637   0.00569   0.00174  -0.1317   0.6923   0.6570
   3.000   0.7662   0.00687   0.00223  -0.1265   0.5320   0.6681
   3.250   0.7698   0.00828   0.00281  -0.1220   0.3460   0.6797
   3.500   0.7806   0.00945   0.00333  -0.1190   0.1991   0.6922
   3.750   0.7985   0.01018   0.00373  -0.1174   0.1178   0.7053
   4.000   0.8185   0.01078   0.00410  -0.1160   0.0639   0.7192
   4.250   0.8399   0.01128   0.00447  -0.1150   0.0305   0.7335
   4.500   0.8601   0.01196   0.00511  -0.1133   0.0063   0.7482
   4.750   0.8833   0.01234   0.00559  -0.1124   0.0056   0.7638
   5.000   0.9063   0.01274   0.00607  -0.1115   0.0049   0.7802
   5.250   0.9281   0.01322   0.00666  -0.1103   0.0043   0.7971
   5.500   0.9488   0.01382   0.00744  -0.1089   0.0040   0.8155
   5.750   0.9677   0.01461   0.00839  -0.1071   0.0038   0.8356
   6.000   0.9843   0.01570   0.00967  -0.1048   0.0036   0.8580
   6.250   0.9993   0.01762   0.01184  -0.1023   0.0034   0.8830
   6.500   1.0168   0.01752   0.01187  -0.1001   0.0032   0.9273
   6.750   1.0364   0.01798   0.01244  -0.0985   0.0031   1.0000
   7.000   1.0597   0.01884   0.01338  -0.0978   0.0028   1.0000
   7.250   1.0828   0.01995   0.01459  -0.0970   0.0025   1.0000
   7.500   1.1061   0.02168   0.01649  -0.0962   0.0024   1.0000
   7.750   1.1290   0.02420   0.01928  -0.0952   0.0023   1.0000
   8.000   1.1466   0.02857   0.02413  -0.0930   0.0025   1.0000
   8.500   1.1576   0.03942   0.03591  -0.0847   0.0042   1.0000
   8.750   1.1599   0.04267   0.03942  -0.0811   0.0042   1.0000
   9.000   1.1591   0.04571   0.04269  -0.0774   0.0041   1.0000
   9.250   1.1538   0.04876   0.04595  -0.0732   0.0040   1.0000
   9.500   1.1415   0.05151   0.04891  -0.0681   0.0040   1.0000
   9.750   1.1265   0.05438   0.05196  -0.0633   0.0039   1.0000
  10.000   1.1094   0.05771   0.05546  -0.0591   0.0039   1.0000
  10.250   1.0909   0.06148   0.05939  -0.0557   0.0039   1.0000
  10.500   1.0710   0.06571   0.06379  -0.0532   0.0039   1.0000
  10.750   1.0500   0.07058   0.06881  -0.0518   0.0039   1.0000
  11.000   1.0277   0.07632   0.07467  -0.0516   0.0039   1.0000
  11.250   1.0037   0.08323   0.08173  -0.0531   0.0039   1.0000
  11.500   0.9769   0.09233   0.09098  -0.0573   0.0040   1.0000
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