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EPPLER 377 (MODIFIED) AIRFOIL (e377m-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 377 (MODIFIED) AIRFOIL (e377m-il)
Reynolds number: 200,000
Max Cl/Cd: 86.41 at α=9°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e377m-il-200000.txt
Download as CSV file: xf-e377m-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 377 (MODIFIED) AIRFOIL                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.1995   0.10089   0.09787  -0.0169   1.0000   0.0147
  -7.500  -0.1941   0.09890   0.09595  -0.0172   1.0000   0.0150
  -7.250  -0.1898   0.09709   0.09424  -0.0174   1.0000   0.0153
  -7.000  -0.1636   0.09357   0.09075  -0.0232   0.9802   0.0158
  -6.750  -0.1250   0.08951   0.08664  -0.0320   0.9516   0.0165
  -6.500  -0.0850   0.08678   0.08382  -0.0411   0.9168   0.0171
  -6.250  -0.0567   0.08527   0.08218  -0.0469   0.8814   0.0173
  -6.000  -0.0368   0.08388   0.08065  -0.0503   0.8523   0.0174
  -5.750  -0.0161   0.08239   0.07903  -0.0537   0.8276   0.0175
  -5.500  -0.0058   0.07764   0.07422  -0.0535   0.8109   0.0177
  -5.250   0.0020   0.07321   0.06971  -0.0523   0.7953   0.0182
  -5.000   0.0182   0.07053   0.06692  -0.0536   0.7796   0.0188
  -4.750   0.0376   0.06807   0.06436  -0.0557   0.7662   0.0197
  -4.500   0.0595   0.06574   0.06194  -0.0583   0.7530   0.0213
  -4.250   0.0857   0.06351   0.05963  -0.0617   0.7412   0.0236
  -4.000   0.1276   0.06300   0.05897  -0.0684   0.7295   0.0250
  -3.750   0.1683   0.06222   0.05802  -0.0748   0.7194   0.0252
  -3.500   0.1971   0.05917   0.05489  -0.0784   0.7103   0.0255
  -3.250   0.2046   0.05395   0.04967  -0.0771   0.7024   0.0263
  -3.000   0.2269   0.05121   0.04683  -0.0786   0.6945   0.0273
  -2.750   0.2553   0.04896   0.04451  -0.0814   0.6858   0.0289
  -2.500   0.2867   0.04685   0.04226  -0.0844   0.6791   0.0311
  -2.250   0.3312   0.04592   0.04120  -0.0895   0.6705   0.0349
  -2.000   0.3757   0.04430   0.03936  -0.0948   0.6641   0.0360
  -1.750   0.3933   0.04061   0.03569  -0.0952   0.6568   0.0374
  -1.500   0.4219   0.03864   0.03359  -0.0970   0.6508   0.0395
  -1.250   0.4549   0.03694   0.03182  -0.0995   0.6438   0.0424
  -1.000   0.5018   0.03702   0.03163  -0.1032   0.6374   0.0467
  -0.750   0.5399   0.03535   0.02981  -0.1061   0.6310   0.0475
  -0.500   0.5595   0.03213   0.02659  -0.1066   0.6252   0.0495
  -0.250   0.5896   0.03087   0.02520  -0.1078   0.6200   0.0555
   0.000   0.6381   0.03213   0.02617  -0.1103   0.6131   0.0588
   0.250   0.6598   0.02852   0.02254  -0.1112   0.6082   0.0602
   0.500   0.6877   0.02710   0.02107  -0.1121   0.6025   0.0626
   0.750   0.7191   0.02617   0.02002  -0.1130   0.5968   0.0671
   1.000   0.7598   0.02675   0.02023  -0.1138   0.5921   0.0704
   1.250   0.7831   0.02418   0.01775  -0.1146   0.5861   0.0729
   1.500   0.8184   0.02477   0.01808  -0.1147   0.5809   0.0815
   1.750   0.8490   0.02343   0.01657  -0.1153   0.5764   0.0820
   2.000   0.8760   0.02182   0.01495  -0.1158   0.5705   0.0834
   2.250   0.9045   0.02105   0.01406  -0.1159   0.5658   0.0893
   2.500   0.9366   0.02134   0.01410  -0.1156   0.5610   0.1051
   2.750   0.9644   0.02027   0.01296  -0.1159   0.5554   0.1184
   3.000   0.9926   0.01989   0.01240  -0.1157   0.5508   0.1299
   3.250   1.0201   0.01958   0.01202  -0.1157   0.5458   0.1414
   3.750   1.0738   0.01869   0.01103  -0.1156   0.5359   0.1596
   4.000   1.1008   0.01871   0.01103  -0.1154   0.5304   0.1774
   4.250   1.1273   0.01835   0.01067  -0.1153   0.5248   0.1915
   4.500   1.1540   0.01821   0.01041  -0.1151   0.5204   0.2157
   4.750   1.1796   0.01802   0.01032  -0.1150   0.5137   0.2536
   5.000   1.2056   0.01755   0.00991  -0.1148   0.5081   0.2902
   5.250   1.2318   0.01739   0.00980  -0.1146   0.5019   0.3125
   5.500   1.2582   0.01736   0.00978  -0.1142   0.4952   0.3210
   5.750   1.2845   0.01736   0.00979  -0.1138   0.4893   0.3183
   6.000   1.3107   0.01756   0.01004  -0.1132   0.4820   0.2900
   6.250   1.3373   0.01777   0.01023  -0.1127   0.4759   0.2647
   6.500   1.3629   0.01789   0.01045  -0.1121   0.4678   0.2360
   6.750   1.3887   0.01795   0.01051  -0.1115   0.4607   0.2190
   7.000   1.4139   0.01798   0.01063  -0.1109   0.4520   0.2104
   7.250   1.4393   0.01801   0.01075  -0.1104   0.4433   0.2063
   7.500   1.4646   0.01799   0.01078  -0.1099   0.4346   0.2091
   7.750   1.4886   0.01801   0.01098  -0.1092   0.4236   0.2100
   8.000   1.5125   0.01803   0.01112  -0.1085   0.4122   0.2086
   8.250   1.5361   0.01808   0.01127  -0.1078   0.3999   0.2087
   8.500   1.5593   0.01818   0.01147  -0.1070   0.3857   0.2097
   8.750   1.5818   0.01832   0.01175  -0.1062   0.3684   0.2116
   9.000   1.6029   0.01855   0.01201  -0.1052   0.3433   0.2141
   9.250   1.6213   0.01903   0.01241  -0.1040   0.3070   0.2209
   9.500   1.6365   0.01999   0.01318  -0.1026   0.2591   0.2258
   9.750   1.6462   0.02153   0.01441  -0.1007   0.2094   0.2284
  10.000   1.6533   0.02329   0.01590  -0.0987   0.1668   0.2316
  10.250   1.6581   0.02512   0.01751  -0.0965   0.1299   0.2350
  10.500   1.6610   0.02693   0.01922  -0.0940   0.1024   0.2386
  10.750   1.6590   0.02876   0.02095  -0.0908   0.0801   0.2421
  11.000   1.6488   0.03118   0.02324  -0.0873   0.0569   0.2449
  11.250   1.6324   0.03462   0.02653  -0.0846   0.0350   0.2461
  11.500   1.6177   0.03850   0.03037  -0.0829   0.0244   0.2480
  11.750   1.6056   0.04256   0.03450  -0.0820   0.0204   0.2501
  12.000   1.5995   0.04617   0.03830  -0.0815   0.0184   0.2556
  12.250   1.5923   0.05007   0.04236  -0.0813   0.0169   0.2639
  12.750   1.5755   0.05805   0.05127  -0.0818   0.0153   1.0000
  13.000   1.5638   0.06286   0.05621  -0.0821   0.0147   1.0000
  13.250   1.5522   0.06770   0.06119  -0.0824   0.0143   1.0000
  13.500   1.5400   0.07268   0.06630  -0.0827   0.0139   1.0000
  13.750   1.5358   0.07667   0.07040  -0.0828   0.0136   1.0000
  14.000   1.5339   0.08045   0.07432  -0.0831   0.0131   1.0000
  14.250   1.5321   0.08432   0.07832  -0.0835   0.0124   1.0000
  14.500   1.5299   0.08832   0.08246  -0.0841   0.0117   1.0000
  14.750   1.5275   0.09239   0.08665  -0.0847   0.0112   1.0000
  15.000   1.5254   0.09641   0.09080  -0.0851   0.0109   1.0000
  15.250   1.5237   0.10046   0.09499  -0.0856   0.0106   1.0000
  15.500   1.5216   0.10466   0.09934  -0.0862   0.0104   1.0000
  15.750   1.5190   0.10904   0.10393  -0.0870   0.0103   1.0000
  16.000   1.5152   0.11377   0.10885  -0.0881   0.0102   1.0000
  16.250   1.5100   0.11895   0.11423  -0.0897   0.0101   1.0000
  16.500   1.5031   0.12460   0.12009  -0.0918   0.0101   1.0000
  16.750   1.4946   0.13076   0.12648  -0.0945   0.0101   1.0000
  17.000   1.4846   0.13743   0.13337  -0.0979   0.0101   1.0000
  17.250   1.4735   0.14463   0.14080  -0.1018   0.0103   1.0000
  17.500   1.4614   0.15235   0.14876  -0.1063   0.0104   1.0000
  17.750   1.4485   0.16056   0.15718  -0.1115   0.0106   1.0000
  18.000   1.4340   0.16962   0.16646  -0.1175   0.0107   1.0000
  18.250   1.4190   0.17933   0.17636  -0.1241   0.0109   1.0000
  18.500   1.4029   0.19014   0.18736  -0.1316   0.0111   1.0000
  18.750   1.3858   0.20221   0.19955  -0.1399   0.0114   1.0000
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