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EPPLER 817 HYDROFOIL AIRFOIL (e817-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 817 HYDROFOIL AIRFOIL (e817-il)
Reynolds number: 1,000,000
Max Cl/Cd: 112.36 at α=1.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e817-il-1000000-n5.txt
Download as CSV file: xf-e817-il-1000000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.5202   0.08328   0.08158  -0.0687   0.9927   0.0015
 -12.000  -0.5307   0.07516   0.07338  -0.0741   0.9907   0.0015
 -11.750  -0.5480   0.06570   0.06381  -0.0813   0.9879   0.0015
 -11.500  -0.5667   0.05614   0.05408  -0.0900   0.9844   0.0015
 -11.000  -0.5866   0.04243   0.04002  -0.1039   0.9718   0.0014
 -10.750  -0.5843   0.03712   0.03449  -0.1110   0.9649   0.0014
 -10.500  -0.5764   0.03068   0.02768  -0.1213   0.9570   0.0014
 -10.250  -0.5684   0.02587   0.02246  -0.1276   0.9429   0.0014
 -10.000  -0.5585   0.02371   0.02005  -0.1284   0.9314   0.0014
  -9.750  -0.5519   0.02142   0.01747  -0.1275   0.9215   0.0013
  -9.500  -0.5400   0.01965   0.01546  -0.1267   0.9147   0.0013
  -9.250  -0.5259   0.01814   0.01373  -0.1258   0.9088   0.0013
  -9.000  -0.5097   0.01671   0.01209  -0.1250   0.9040   0.0013
  -8.750  -0.4916   0.01550   0.01072  -0.1244   0.8999   0.0013
  -8.500  -0.4713   0.01450   0.00953  -0.1240   0.8959   0.0013
  -8.250  -0.4497   0.01356   0.00843  -0.1237   0.8924   0.0013
  -8.000  -0.4265   0.01275   0.00748  -0.1236   0.8897   0.0013
  -7.750  -0.4024   0.01205   0.00667  -0.1236   0.8871   0.0013
  -7.500  -0.3773   0.01143   0.00593  -0.1236   0.8846   0.0013
  -7.250  -0.3513   0.01093   0.00534  -0.1237   0.8823   0.0014
  -7.000  -0.3248   0.01047   0.00477  -0.1239   0.8802   0.0014
  -6.750  -0.2978   0.01011   0.00432  -0.1241   0.8783   0.0015
  -6.500  -0.2703   0.00979   0.00393  -0.1244   0.8766   0.0017
  -6.250  -0.2429   0.00952   0.00360  -0.1246   0.8747   0.0018
  -6.000  -0.2152   0.00928   0.00329  -0.1249   0.8728   0.0023
  -5.750  -0.1875   0.00901   0.00301  -0.1251   0.8708   0.0050
  -5.500  -0.1601   0.00860   0.00269  -0.1255   0.8690   0.0240
  -5.250  -0.1322   0.00831   0.00246  -0.1259   0.8674   0.0417
  -5.000  -0.1045   0.00784   0.00216  -0.1264   0.8659   0.0866
  -4.750  -0.0774   0.00696   0.00176  -0.1273   0.8644   0.2068
  -4.500  -0.0491   0.00668   0.00163  -0.1278   0.8630   0.2496
  -4.250  -0.0206   0.00658   0.00152  -0.1281   0.8615   0.2619
  -4.000   0.0080   0.00645   0.00143  -0.1285   0.8599   0.2817
  -3.750   0.0365   0.00631   0.00136  -0.1289   0.8583   0.3030
  -3.500   0.0652   0.00622   0.00130  -0.1292   0.8568   0.3194
  -3.250   0.0940   0.00615   0.00124  -0.1296   0.8554   0.3299
  -3.000   0.1229   0.00609   0.00118  -0.1299   0.8541   0.3386
  -2.750   0.1518   0.00605   0.00114  -0.1303   0.8528   0.3475
  -2.500   0.1808   0.00601   0.00110  -0.1307   0.8514   0.3558
  -2.250   0.2097   0.00597   0.00108  -0.1310   0.8501   0.3651
  -2.000   0.2384   0.00593   0.00106  -0.1313   0.8487   0.3743
  -1.750   0.2670   0.00589   0.00105  -0.1317   0.8472   0.3826
  -1.500   0.2957   0.00584   0.00105  -0.1320   0.8454   0.3921
  -1.250   0.3244   0.00581   0.00104  -0.1322   0.8434   0.4021
  -1.000   0.3530   0.00577   0.00104  -0.1325   0.8410   0.4113
  -0.750   0.3818   0.00575   0.00104  -0.1328   0.8385   0.4203
  -0.500   0.4101   0.00572   0.00105  -0.1330   0.8352   0.4305
  -0.250   0.4381   0.00568   0.00105  -0.1331   0.8309   0.4412
   0.000   0.4664   0.00565   0.00105  -0.1332   0.8260   0.4507
   0.250   0.4944   0.00563   0.00108  -0.1333   0.8209   0.4606
   0.500   0.5222   0.00560   0.00110  -0.1333   0.8147   0.4715
   0.750   0.5499   0.00558   0.00111  -0.1333   0.8074   0.4820
   1.000   0.5773   0.00557   0.00113  -0.1332   0.7978   0.4918
   1.250   0.6042   0.00556   0.00115  -0.1331   0.7850   0.5025
   1.500   0.6292   0.00560   0.00118  -0.1324   0.7556   0.5132
   1.750   0.6440   0.00609   0.00128  -0.1296   0.6587   0.5233
   2.000   0.6536   0.00701   0.00165  -0.1259   0.5305   0.5326
   2.250   0.6678   0.00781   0.00200  -0.1234   0.4178   0.5427
   2.500   0.6881   0.00830   0.00225  -0.1221   0.3530   0.5537
   3.000   0.7284   0.00934   0.00281  -0.1195   0.2191   0.5765
   3.250   0.7461   0.01009   0.00322  -0.1178   0.1279   0.5874
   3.500   0.7656   0.01074   0.00358  -0.1164   0.0606   0.5988
   3.750   0.7890   0.01109   0.00386  -0.1157   0.0372   0.6106
   4.000   0.8130   0.01139   0.00413  -0.1151   0.0229   0.6230
   4.250   0.8358   0.01179   0.00447  -0.1142   0.0073   0.6352
   4.500   0.8593   0.01215   0.00487  -0.1134   0.0033   0.6478
   4.750   0.8835   0.01244   0.00524  -0.1127   0.0031   0.6608
   5.000   0.9073   0.01275   0.00564  -0.1120   0.0028   0.6743
   5.250   0.9309   0.01308   0.00604  -0.1113   0.0025   0.6879
   5.500   0.9543   0.01341   0.00648  -0.1105   0.0023   0.7017
   5.750   0.9774   0.01377   0.00690  -0.1097   0.0020   0.7160
   6.000   0.9999   0.01419   0.00740  -0.1088   0.0019   0.7302
   6.250   1.0219   0.01466   0.00797  -0.1078   0.0018   0.7442
   6.500   1.0434   0.01518   0.00859  -0.1067   0.0017   0.7584
   6.750   1.0640   0.01580   0.00933  -0.1054   0.0016   0.7741
   7.000   1.0833   0.01658   0.01025  -0.1039   0.0015   0.7918
   7.250   1.0996   0.01788   0.01177  -0.1018   0.0013   0.8106
   7.500   1.1197   0.01847   0.01249  -0.1005   0.0013   0.8332
   7.750   1.1392   0.01898   0.01313  -0.0991   0.0012   0.8598
   8.000   1.1563   0.01940   0.01371  -0.0971   0.0012   0.8968
   8.250   1.1689   0.01975   0.01426  -0.0942   0.0012   1.0000
   8.500   1.1887   0.02049   0.01508  -0.0929   0.0011   1.0000
   8.750   1.2078   0.02133   0.01601  -0.0916   0.0010   1.0000
   9.000   1.2264   0.02225   0.01704  -0.0903   0.0010   1.0000
   9.250   1.2438   0.02334   0.01826  -0.0887   0.0009   1.0000
   9.500   1.2600   0.02465   0.01972  -0.0870   0.0008   1.0000
   9.750   1.2748   0.02610   0.02134  -0.0851   0.0008   1.0000
  10.000   1.2873   0.02782   0.02327  -0.0829   0.0007   1.0000
  10.250   1.2966   0.02980   0.02548  -0.0803   0.0007   1.0000
  10.500   1.3024   0.03204   0.02798  -0.0773   0.0007   1.0000
  10.750   1.3035   0.03463   0.03084  -0.0738   0.0006   1.0000
  11.000   1.2987   0.03772   0.03425  -0.0698   0.0006   1.0000
  11.250   1.2877   0.04134   0.03818  -0.0655   0.0006   1.0000
  11.500   1.2686   0.04581   0.04300  -0.0610   0.0006   1.0000
  11.750   1.2418   0.05122   0.04875  -0.0568   0.0006   1.0000
  12.000   1.2107   0.05741   0.05525  -0.0536   0.0006   1.0000
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